From 09119bc9c58d47be9de2456d5d0fec7522f0bb12 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Mon, 4 Aug 2025 11:24:35 +0200 Subject: [PATCH 01/26] adding a pyramid_model, initial commit --- examples/pyramid_model.jl | 5 +++++ 1 file changed, 5 insertions(+) create mode 100644 examples/pyramid_model.jl diff --git a/examples/pyramid_model.jl b/examples/pyramid_model.jl new file mode 100644 index 00000000..d6fa9a4e --- /dev/null +++ b/examples/pyramid_model.jl @@ -0,0 +1,5 @@ +#= + +Example script to run the VortexStepMethod on a pyramid model. + +=# \ No newline at end of file From a0d99779bd482f1b50319db026317d8cf0c2c551 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Mon, 4 Aug 2025 11:26:35 +0200 Subject: [PATCH 02/26] #183 testing commit --- examples/pyramid_model.jl | 2 ++ 1 file changed, 2 insertions(+) diff --git a/examples/pyramid_model.jl b/examples/pyramid_model.jl index d6fa9a4e..c6778e9c 100644 --- a/examples/pyramid_model.jl +++ b/examples/pyramid_model.jl @@ -2,4 +2,6 @@ Example script to run the VortexStepMethod on a pyramid model. +Second commit + =# \ No newline at end of file From f9c7c802595acf20d23f72aa79f39ae694218f66 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Mon, 4 Aug 2025 11:28:05 +0200 Subject: [PATCH 03/26] #185, this commit/issue number work? --- examples/pyramid_model.jl | 2 ++ 1 file changed, 2 insertions(+) diff --git a/examples/pyramid_model.jl b/examples/pyramid_model.jl index c6778e9c..5baf7974 100644 --- a/examples/pyramid_model.jl +++ b/examples/pyramid_model.jl @@ -4,4 +4,6 @@ Example script to run the VortexStepMethod on a pyramid model. Second commit +Third test commit + =# \ No newline at end of file From 1ba7681bb6cfe098cd2da55502e7478b5bac5231 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Mon, 4 Aug 2025 12:05:12 +0200 Subject: [PATCH 04/26] #185 Create rectangular wing from yaml and plot, using csv polar input --- data/pyramid_model/polars/1.csv | 5 ++ data/pyramid_model/polars/2.csv | 5 ++ data/pyramid_model/pyramid.yaml | 50 +++++++++++ examples/menu.jl | 4 +- examples/pyramid_model.jl | 147 +++++++++++++++++++++++++++++-- examples/ram_air_kite_v2.jl | 148 ++++++++++++++++++++++++++++++++ 6 files changed, 353 insertions(+), 6 deletions(-) create mode 100644 data/pyramid_model/polars/1.csv create mode 100644 data/pyramid_model/polars/2.csv create mode 100644 data/pyramid_model/pyramid.yaml create mode 100644 examples/ram_air_kite_v2.jl diff --git a/data/pyramid_model/polars/1.csv b/data/pyramid_model/polars/1.csv new file mode 100644 index 00000000..f2038e07 --- /dev/null +++ b/data/pyramid_model/polars/1.csv @@ -0,0 +1,5 @@ +alpha,cl,cd,cm +-10.0,0.1,0.01,0.0 +-5.0,0.5,0.012,0.02 +0.0,0.8,0.015,0.04 +5.0,1.1,0.018,0.06 \ No newline at end of file diff --git a/data/pyramid_model/polars/2.csv b/data/pyramid_model/polars/2.csv new file mode 100644 index 00000000..f2038e07 --- /dev/null +++ b/data/pyramid_model/polars/2.csv @@ -0,0 +1,5 @@ +alpha,cl,cd,cm +-10.0,0.1,0.01,0.0 +-5.0,0.5,0.012,0.02 +0.0,0.8,0.015,0.04 +5.0,1.1,0.018,0.06 \ No newline at end of file diff --git a/data/pyramid_model/pyramid.yaml b/data/pyramid_model/pyramid.yaml new file mode 100644 index 00000000..594b4425 --- /dev/null +++ b/data/pyramid_model/pyramid.yaml @@ -0,0 +1,50 @@ +wing_sections: + # --------------------------------------------------------------- + # headers: + # - airfoil_id: integer, unique identifier for the airfoil (matches wing_airfoils) + # - LE_x: x-coordinate of leading edge + # - LE_y: y-coordinate of leading edge + # - LE_z: z-coordinate of leading edge + # - TE_x: x-coordinate of trailing edge + # - TE_y: y-coordinate of trailing edge + # - TE_z: z-coordinate of trailing edge + # --------------------------------------------------------------- + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0, 10, 0, 1, 10, 0] + - [2, 0, -10, 0, 1, -10, 0] + +wing_airfoils: + # --------------------------------------------------------------- + # headers: + # - airfoil_id: integer, unique identifier for the airfoil + # - type: one of [neuralfoil, breukels_regression, masure_regression, polars] + # - info_dict: dictionary with parameters depending on 'type' + # + # info_dict fields by type: + # - breukels_regression: + # t: Tube diameter non-dimensionalized by chord (required) + # kappa: Maximum camber height/magnitude, non-dimensionalized by chord (required) + # - neuralfoil: + # dat_file_path: Path to airfoil .dat file (x, y columns) + # model_size: NeuralFoil model size (e.g., "xxxlarge") + # xtr_lower: Lower transition location (0=forced, 1=free) + # xtr_upper: Upper transition location + # n_crit: Critical amplification factor (see guidelines below) + # n_crit guidelines: + # Sailplane: 12–14 + # Motorglider: 11–13 + # Clean wind tunnel: 10–12 + # Average wind tunnel: 9 (standard "e^9 method") + # Dirty wind tunnel: 4–8 + # - polars: + # csv_file_path: Path to polar CSV file (columns: alpha [rad], cl, cd, cm) + # - masure_regression: + # t, eta, kappa, delta, lamba, phi: Regression parameters + # --------------------------------------------------------------- + alpha_range: [-10, 31, 0.5] # [deg], in this range the polars are calculated + reynolds: !!float 1e6 # Reynolds number + headers: [airfoil_id, type, info_dict] + data: + - [1, breukels_regression, {t: 0.3225132246121334, kappa: 0.0405837}] + - [2, breukels_regression, {t: 0.1837401335882308, kappa: 0.043495}] \ No newline at end of file diff --git a/examples/menu.jl b/examples/menu.jl index ee4ba929..2160ca85 100644 --- a/examples/menu.jl +++ b/examples/menu.jl @@ -9,7 +9,9 @@ using REPL.TerminalMenus url = "https://opensourceawe.github.io/VortexStepMethod.jl/dev" -options = ["rectangular_wing = include(\"rectangular_wing.jl\")", +options = [ + "pyramid_model = include(\"pyramid_model.jl\")", + "rectangular_wing = include(\"rectangular_wing.jl\")", "ram_air_kite = include(\"ram_air_kite.jl\")", "stall_model = include(\"stall_model.jl\")", "bench = include(\"bench.jl\")", diff --git a/examples/pyramid_model.jl b/examples/pyramid_model.jl index 5baf7974..9df25b40 100644 --- a/examples/pyramid_model.jl +++ b/examples/pyramid_model.jl @@ -1,9 +1,146 @@ -#= +using LinearAlgebra +using VortexStepMethod +using ControlPlots +using YAML +using CSV +using DataFrames -Example script to run the VortexStepMethod on a pyramid model. -Second commit +function read_yaml(yaml_file_path) + # Read the YAML file to get the sections + yaml_data = YAML.load_file(yaml_file_path) + + # Extract headers and data + headers = yaml_data["wing_sections"]["headers"] + data_rows = yaml_data["wing_sections"]["data"] + + # Convert YAML data to the expected format + sections = [] + for row in data_rows + # Create a dictionary mapping headers to values + section_dict = Dict(zip(headers, row)) + + # Keep airfoil_id as integer for CSV filename lookup + airfoil_id = section_dict["airfoil_id"] + + # Extract coordinates + le_coord = [section_dict["LE_x"], section_dict["LE_y"], section_dict["LE_z"]] + te_coord = [section_dict["TE_x"], section_dict["TE_y"], section_dict["TE_z"]] + + section = ( + airfoil_id = airfoil_id, + le_coord = le_coord, + te_coord = te_coord + ) + push!(sections, section) + end -Third test commit + return sections +end -=# \ No newline at end of file +function load_polar_data(airfoil_id, polars_dir) + """ + Load polar data from CSV file for given airfoil_id. + Expected CSV format: columns named alpha, cl, cd, cm + """ + csv_filename = "$(airfoil_id).csv" + csv_filepath = joinpath(polars_dir, csv_filename) + + if !isfile(csv_filepath) + @warn "Polar file not found: $csv_filepath. Using INVISCID model instead." + return nothing, INVISCID + end + + try + df = CSV.read(csv_filepath, DataFrame) + + # Verify required columns exist + required_cols = ["alpha", "cl", "cd", "cm"] + missing_cols = setdiff(required_cols, names(df)) + if !isempty(missing_cols) + @warn "Missing columns $missing_cols in $csv_filepath. Using INVISCID model instead." + return nothing, INVISCID + end + + # Create aero_data tuple + aero_data = (df.alpha, df.cl, df.cd, df.cm) + return aero_data, POLAR_VECTORS + + catch e + @warn "Error reading polar file $csv_filepath: $e. Using INVISCID model instead." + return nothing, INVISCID + end +end + + +function instantiate_from_yaml(yaml_file_path, polars_dir; n_panels=20, spanwise_distribution=LINEAR) + """ + Create a wing geometry from YAML file with polar data loaded from CSV files. + + # Arguments + - `yaml_file_path`: Path to YAML file containing wing section definitions + - `polars_dir`: Path to directory containing polar CSV files (named .csv) + - `n_panels`: Number of panels for the wing (default: 20) + - `spanwise_distribution`: Panel distribution type (default: LINEAR) + + # Returns + - `BodyAerodynamics`: Initialized aerodynamics object containing the wing + + # Example + ```julia + yaml_path = "pyramid.yaml" + polars_dir = "/path/to/polars" + body_aero = instantiate_from_yaml(yaml_path, polars_dir; n_panels=30) + ``` + """ + # Create wing with specified panel distribution + wing = Wing(n_panels, spanwise_distribution=spanwise_distribution) + + # Read sections from YAML file + sections = read_yaml(yaml_file_path) + + # Add each section to the wing + for section in sections + # Load polar data for this airfoil + aero_data, aero_model = load_polar_data(section.airfoil_id, polars_dir) + + println("Section airfoil_id $(section.airfoil_id): Using $(aero_model) model") + + add_section!(wing, + section.le_coord, # Leading edge coordinate + section.te_coord, # Trailing edge coordinate + aero_model, # Aerodynamic model (POLAR_VECTORS or INVISCID) + aero_data) # Aerodynamic data tuple or nothing + end + + # Initialize and return aerodynamics object + body_aero = BodyAerodynamics([wing]) + return body_aero +end + +# getting the project_dir +project_dir = dirname(dirname(pathof(VortexStepMethod))) # Go up one level from src to project root +yaml_file_path = joinpath(project_dir, "data", "pyramid_model", "pyramid.yaml") +polars_dir = joinpath(project_dir, "data", "pyramid_model", "polars") + +sections = read_yaml(yaml_file_path) +println("Read sections from YAML file: $(length(sections)) sections") +println("Sections: $(sections)") + +body_aero = instantiate_from_yaml(yaml_file_path, polars_dir; n_panels=20) +println("Created wing geometry with $(length(body_aero.panels)) panels") + +# Plotting Geometrys +PLOT = true +USE_TEX = false +PLOT && plot_geometry( + body_aero, + ""; + data_type=".svg", + save_path="", + is_save=false, + is_show=true, + view_elevation=15, + view_azimuth=-120, + use_tex=USE_TEX +) \ No newline at end of file diff --git a/examples/ram_air_kite_v2.jl b/examples/ram_air_kite_v2.jl new file mode 100644 index 00000000..d599a2d6 --- /dev/null +++ b/examples/ram_air_kite_v2.jl @@ -0,0 +1,148 @@ +using VortexStepMethod,LinearAlgebra +using ControlPlots # Use plotx instead of Plots + +# --- User-specified parameters --- +wind_speed = 10.0 # [m/s] +angle_of_attack_deg = 5.0 # [deg] +sideslip_deg = 0.0 +yaw_rate = 0.0 # [rad/s] (not used in static analysis) +air_density = 1.225 # [kg/m^3] Air density at sea level + +println("=== Static Aerodynamic Analysis (VSM) ===") +println("Wind speed: $wind_speed m/s") +println("Angle of attack: $angle_of_attack_deg deg") +println("Sideslip: $sideslip_deg deg") + +# --- Setup kite and aero model --- +ram_wing = RamAirWing("data/ram_air_kite_body.obj", "data/ram_air_kite_foil.dat"; align_to_principal=true) +body_aero = BodyAerodynamics([ram_wing]) + +# --- Set apparent wind vector in body axes --- +α = deg2rad(angle_of_attack_deg) +β = deg2rad(sideslip_deg) +va = wind_speed * [ + cos(α)*cos(β), # X_b (forward) + sin(β), # Y_b (right) + sin(α)*cos(β) # Z_b (down) +] +set_va!(body_aero, va) + +# --- Create and run VSM solver --- +solver = Solver(body_aero; + aerodynamic_model_type=VSM, + is_with_artificial_damping=false, + rtol=1e-5, + solver_type=NONLIN +) + +# One can run the solver seperately, given back a Dict{String, Any} +solver = Solver(body_aero; density=air_density) +solve!(solver, body_aero) +forces = solver.sol.force +println("\nType of solver: ", typeof(solver), " Type of forces: ", typeof(forces)) + +# Better to use the VortexStepMethod.solve method, returns a dictionary with the results +results = VortexStepMethod.solve(solver, body_aero; log=true) +println("Type of results: ", typeof(results)) + + +# --- Run over an alpha sweep --- +# using Plots # Add this at the top if you want to plot +alphas = 1:10 +f_xs = Float64[] # Fx over alpha sweep +f_ys = Float64[] # Fy over alpha sweep +f_zs = Float64[] # Fz over alpha sweep +m_xs = Float64[] # Mx over alpha sweep +m_ys = Float64[] # My over alpha sweep +m_zs = Float64[] # Mz over alpha sweep + +for alpha in alphas + local_α = deg2rad(alpha) + local_β = deg2rad(sideslip_deg) + local_va = wind_speed * [ + cos(local_α)*cos(local_β), + sin(local_β), + sin(local_α)*cos(local_β) + ] + set_va!(body_aero, local_va) + + solve!(solver, body_aero) + results_i = VortexStepMethod.solve(solver, body_aero; log=true) + + push!(f_xs, results_i["Fx"]) + push!(f_ys, results_i["Fy"]) + push!(f_zs, results_i["Fz"]) + push!(m_xs, results_i["Mx"]) + push!(m_ys, results_i["My"]) + push!(m_zs, results_i["Mz"]) + +end + + +# --- Plot results: true multi-row plotx style as in simple_lin_model.jl --- +p = plotx( + alphas, + f_xs, + f_ys, + f_zs, + m_xs, + m_ys, + m_zs; + ylabels=["Fx [N]", "Fy [N]", "Fz [N]", "Mx [Nm]", "My [Nm]", "Mz [Nm]"], + xlabel="alpha [deg]", + fig="Aerodynamic Forces and Moments" +) +display(p) + + +# Using plotting modules, to create more comprehensive plots +PLOT = true +USE_TEX = false + + +# Plotting geometry +PLOT && plot_geometry( + body_aero, + ""; + data_type=".svg", + save_path="", + is_save=false, + is_show=true, + view_elevation=15, + view_azimuth=-120, + use_tex=USE_TEX +) + +# Plotting polars +PLOT && plot_polars( + [solver], + [body_aero], + ["VSM from Ram Air Kite OBJ and DAT file"], + angle_range=range(0, 20, length=20), + angle_type="angle_of_attack", + angle_of_attack=5, + side_slip=0, + v_a=10, + title="ram_kite_panels_$(ram_wing.n_panels)_distribution_$(ram_wing.spanwise_distribution)", + data_type=".pdf", + is_save=false, + is_show=true, + use_tex=USE_TEX +) + +# Plotting spanwise distributions +body_y_coordinates = [panel.aero_center[2] for panel in body_aero.panels] + +PLOT && plot_distribution( + [body_y_coordinates], + [results], + ["VSM"]; + title="CAD_spanwise_distributions_alpha_$(round(angle_of_attack_deg, digits=1))_delta_$(round(sideslip_deg, digits=1))_yaw_$(round(yaw_rate, digits=1))_v_a_$(round(wind_speed, digits=1))", + data_type=".pdf", + is_save=false, + is_show=true, + use_tex=USE_TEX +) + + +nothing \ No newline at end of file From b08dd6e7773b8d4590c9d1c2b496c62d06d8b433 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Mon, 4 Aug 2025 15:04:58 +0200 Subject: [PATCH 05/26] #185 added yaml_geometry: enabling one to run VSM defined from a yaml file. --- .../{pyramid.yaml => geometry.yaml} | 6 +- data/pyramid_model/polars/1.csv | 76 +++++- data/pyramid_model/polars/2.csv | 76 +++++- data/pyramid_model/vsm_settings.yaml | 36 +++ examples/pyramid_model.jl | 132 +--------- src/VortexStepMethod.jl | 3 +- src/body_aerodynamics.jl | 2 +- src/polars.jl | 1 - src/wing_geometry.jl | 1 - src/yaml_geometry.jl | 227 ++++++++++++++++++ 10 files changed, 418 insertions(+), 142 deletions(-) rename data/pyramid_model/{pyramid.yaml => geometry.yaml} (93%) create mode 100644 data/pyramid_model/vsm_settings.yaml create mode 100644 src/yaml_geometry.jl diff --git a/data/pyramid_model/pyramid.yaml b/data/pyramid_model/geometry.yaml similarity index 93% rename from data/pyramid_model/pyramid.yaml rename to data/pyramid_model/geometry.yaml index 594b4425..a239c433 100644 --- a/data/pyramid_model/pyramid.yaml +++ b/data/pyramid_model/geometry.yaml @@ -41,10 +41,12 @@ wing_airfoils: # csv_file_path: Path to polar CSV file (columns: alpha [rad], cl, cd, cm) # - masure_regression: # t, eta, kappa, delta, lamba, phi: Regression parameters + # - inviscid: + # no further data is required # --------------------------------------------------------------- alpha_range: [-10, 31, 0.5] # [deg], in this range the polars are calculated reynolds: !!float 1e6 # Reynolds number headers: [airfoil_id, type, info_dict] data: - - [1, breukels_regression, {t: 0.3225132246121334, kappa: 0.0405837}] - - [2, breukels_regression, {t: 0.1837401335882308, kappa: 0.043495}] \ No newline at end of file + - [1, polars, {csv_file_path: "polars/1.csv"}] + - [2, polars, {csv_file_path: "polars/2.csv"}] \ No newline at end of file diff --git a/data/pyramid_model/polars/1.csv b/data/pyramid_model/polars/1.csv index f2038e07..618e39b9 100644 --- a/data/pyramid_model/polars/1.csv +++ b/data/pyramid_model/polars/1.csv @@ -1,5 +1,71 @@ -alpha,cl,cd,cm --10.0,0.1,0.01,0.0 --5.0,0.5,0.012,0.02 -0.0,0.8,0.015,0.04 -5.0,1.1,0.018,0.06 \ No newline at end of file +alpha,Cd,Cs,Cl,Cm +-10.0,0.0249065318608897,-3.434761974054366e-21,-1.0732064541182402,0.0054067639622245 +-9.5,0.0236873271741019,-3.285535810591269e-21,-1.0370727681402363,0.0058564293781756 +-9.0,0.0225262393305432,-3.1355323293482928e-21,-0.9992907398617008,0.0062213900212979 +-8.5,0.0214269325718191,-2.984782761608788e-21,-0.9599576821061372,0.0065104482864488 +-8.0,0.0203930711395351,-2.833318338656105e-21,-0.9191709076970505,0.006732406568486 +-7.5,0.0194283192752969,-2.6811702917735944e-21,-0.8770277294579452,0.0068960672622671 +-7.0,0.01853634122071,-2.528369852244608e-21,-0.8336254602123256,0.0070102327626497 +-6.5,0.0177208012173799,-2.3749482513524935e-21,-0.7890614127836962,0.0070837054644914 +-6.0,0.0169853635069124,-2.2209367203806045e-21,-0.7434328999955613,0.0071252877626499 +-5.5,0.0163336923309129,-2.06636649061229e-21,-0.6968372346714253,0.0071437820519827 +-5.0,0.0157694519309871,-1.9112687933309017e-21,-0.6493717296347931,0.0071479907273476 +-4.5,0.0152645128216272,-1.753587209885578e-21,-0.5997295153722275,0.0070196560505497 +-4.0,0.01479533503566,-1.5927577702719893e-21,-0.5471734663994646,0.0066920925435352 +-3.5,0.0143724670921928,-1.4310503787432801e-21,-0.4926555115837663,0.0062514609913727 +-3.0,0.0140064575103327,-1.2707349395525959e-21,-0.4371275797923952,0.0057839221791311 +-2.5,0.0137078548091868,-1.1140813569530825e-21,-0.3815415998926136,0.005375636891879 +-2.0,0.0134872075078624,-9.63359535197884e-22,-0.326849500751684,0.0051127659146851 +-1.5,0.0133110016081565,-8.173276016701202e-22,-0.2729636358104737,0.0049791802562241 +-1.0,0.013154948085695,-6.747509165125449e-22,-0.219054658831915,0.0048810850331918 +-0.5,0.0130434329203279,-5.379102331177564e-22,-0.1649619491663683,0.004788142192688 +0.0,0.0130008420919056,-4.090863048783536e-22,-0.1105248861641936,0.0046700136818125 +0.5,0.0130084720389809,-2.8680744793175213e-22,-0.0553123307395135,0.0044698279268781 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+24.5,0.3095803373831047,-4.2435181693311005e-21,0.2682567606245242,-0.3638102022530151 \ No newline at end of file diff --git a/data/pyramid_model/vsm_settings.yaml b/data/pyramid_model/vsm_settings.yaml new file mode 100644 index 00000000..5ae66dc9 --- /dev/null +++ b/data/pyramid_model/vsm_settings.yaml @@ -0,0 +1,36 @@ +Model: + VSM: Vortex Step Method + LLT: Lifting Line Theory +PanelDistribution: + LINEAR: Linear distribution + COSINE: Cosine distribution + COSINE_VAN_GARREL: van Garrel cosine distribution + SPLIT_PROVIDED: Split provided sections + UNCHANGED: Keep original sections +InitialGammaDistribution: + ELLIPTIC: Elliptic distribution + ZEROS: Constant distribution + +wings: + - name: main_wing + n_panels: 40 + n_groups: 40 + spanwise_panel_distribution: LINEAR + spanwise_direction: [0.0, 1.0, 0.0] + remove_nan: true +solver_settings: + n_panels: 40 + n_groups: 40 + aerodynamic_model_type: VSM + density: 1.225 # air density [kg/m³] + max_iterations: 1500 + rtol: 1e-5 # relative error [-] + tol_reference_error: 0.001 + relaxation_factor: 0.03 # relaxation factor for convergence + artificial_damping: false # whether to apply artificial damping + k2: 0.1 # artificial damping parameter + k4: 0.0 # artificial damping parameter + type_initial_gamma_distribution: ELLIPTIC + core_radius_fraction: 1e-20 + mu: 1.81e-5 # dynamic viscosity [N·s/m²] + calc_only_f_and_gamma: false # whether to only output f and gamma diff --git a/examples/pyramid_model.jl b/examples/pyramid_model.jl index 9df25b40..fa48f71e 100644 --- a/examples/pyramid_model.jl +++ b/examples/pyramid_model.jl @@ -1,136 +1,16 @@ using LinearAlgebra using VortexStepMethod using ControlPlots -using YAML -using CSV -using DataFrames - -function read_yaml(yaml_file_path) - # Read the YAML file to get the sections - yaml_data = YAML.load_file(yaml_file_path) - - # Extract headers and data - headers = yaml_data["wing_sections"]["headers"] - data_rows = yaml_data["wing_sections"]["data"] - - # Convert YAML data to the expected format - sections = [] - for row in data_rows - # Create a dictionary mapping headers to values - section_dict = Dict(zip(headers, row)) - - # Keep airfoil_id as integer for CSV filename lookup - airfoil_id = section_dict["airfoil_id"] - - # Extract coordinates - le_coord = [section_dict["LE_x"], section_dict["LE_y"], section_dict["LE_z"]] - te_coord = [section_dict["TE_x"], section_dict["TE_y"], section_dict["TE_z"]] - - section = ( - airfoil_id = airfoil_id, - le_coord = le_coord, - te_coord = te_coord - ) - push!(sections, section) - end - - return sections -end - -function load_polar_data(airfoil_id, polars_dir) - """ - Load polar data from CSV file for given airfoil_id. - Expected CSV format: columns named alpha, cl, cd, cm - """ - csv_filename = "$(airfoil_id).csv" - csv_filepath = joinpath(polars_dir, csv_filename) - - if !isfile(csv_filepath) - @warn "Polar file not found: $csv_filepath. Using INVISCID model instead." - return nothing, INVISCID - end - - try - df = CSV.read(csv_filepath, DataFrame) - - # Verify required columns exist - required_cols = ["alpha", "cl", "cd", "cm"] - missing_cols = setdiff(required_cols, names(df)) - if !isempty(missing_cols) - @warn "Missing columns $missing_cols in $csv_filepath. Using INVISCID model instead." - return nothing, INVISCID - end - - # Create aero_data tuple - aero_data = (df.alpha, df.cl, df.cd, df.cm) - return aero_data, POLAR_VECTORS - - catch e - @warn "Error reading polar file $csv_filepath: $e. Using INVISCID model instead." - return nothing, INVISCID - end -end - - -function instantiate_from_yaml(yaml_file_path, polars_dir; n_panels=20, spanwise_distribution=LINEAR) - """ - Create a wing geometry from YAML file with polar data loaded from CSV files. - - # Arguments - - `yaml_file_path`: Path to YAML file containing wing section definitions - - `polars_dir`: Path to directory containing polar CSV files (named .csv) - - `n_panels`: Number of panels for the wing (default: 20) - - `spanwise_distribution`: Panel distribution type (default: LINEAR) - - # Returns - - `BodyAerodynamics`: Initialized aerodynamics object containing the wing - - # Example - ```julia - yaml_path = "pyramid.yaml" - polars_dir = "/path/to/polars" - body_aero = instantiate_from_yaml(yaml_path, polars_dir; n_panels=30) - ``` - """ - # Create wing with specified panel distribution - wing = Wing(n_panels, spanwise_distribution=spanwise_distribution) - - # Read sections from YAML file - sections = read_yaml(yaml_file_path) - - # Add each section to the wing - for section in sections - # Load polar data for this airfoil - aero_data, aero_model = load_polar_data(section.airfoil_id, polars_dir) - - println("Section airfoil_id $(section.airfoil_id): Using $(aero_model) model") - - add_section!(wing, - section.le_coord, # Leading edge coordinate - section.te_coord, # Trailing edge coordinate - aero_model, # Aerodynamic model (POLAR_VECTORS or INVISCID) - aero_data) # Aerodynamic data tuple or nothing - end - - # Initialize and return aerodynamics object - body_aero = BodyAerodynamics([wing]) - return body_aero -end - -# getting the project_dir +# settings project_dir = dirname(dirname(pathof(VortexStepMethod))) # Go up one level from src to project root -yaml_file_path = joinpath(project_dir, "data", "pyramid_model", "pyramid.yaml") -polars_dir = joinpath(project_dir, "data", "pyramid_model", "polars") - -sections = read_yaml(yaml_file_path) -println("Read sections from YAML file: $(length(sections)) sections") -println("Sections: $(sections)") +yaml_geometry_path = joinpath(project_dir, "data", "pyramid_model", "geometry.yaml") -body_aero = instantiate_from_yaml(yaml_file_path, polars_dir; n_panels=20) -println("Created wing geometry with $(length(body_aero.panels)) panels") +# Create wing geometry from YAML (following RamAirWing pattern) +wing = YamlWing(yaml_geometry_path; n_panels=20, spanwise_distribution=LINEAR) +body_aero = BodyAerodynamics([wing]) -# Plotting Geometrys +# Plotting Geometry PLOT = true USE_TEX = false PLOT && plot_geometry( diff --git a/src/VortexStepMethod.jl b/src/VortexStepMethod.jl index 15d3829b..bedae5f5 100644 --- a/src/VortexStepMethod.jl +++ b/src/VortexStepMethod.jl @@ -26,7 +26,7 @@ using Xfoil # Export public interface export VSMSettings, WingSettings, SolverSettings, vs -export Wing, Section, RamAirWing, reinit! +export Wing, Section, RamAirWing, YamlWing, reinit! export BodyAerodynamics export Solver, solve, solve_base!, solve!, VSMSolution, linearize export calculate_results @@ -270,6 +270,7 @@ include("settings.jl") include("wing_geometry.jl") include("polars.jl") include("ram_geometry.jl") +include("yaml_geometry.jl") include("filament.jl") include("panel.jl") include("body_aerodynamics.jl") diff --git a/src/body_aerodynamics.jl b/src/body_aerodynamics.jl index 6860ac94..50a34fe3 100644 --- a/src/body_aerodynamics.jl +++ b/src/body_aerodynamics.jl @@ -23,7 +23,7 @@ Main structure for calculating aerodynamic properties of bodies. Use the constru """ @with_kw mutable struct BodyAerodynamics{P} panels::Vector{Panel} - wings::Union{Vector{Wing}, Vector{RamAirWing}} + wings::Union{Vector{Wing}, Vector{RamAirWing}, Vector{YamlWing}} _va::MVec3 = zeros(MVec3) omega::MVec3 = zeros(MVec3) gamma_distribution::MVector{P, Float64} = zeros(MVector{P, Float64}) diff --git a/src/polars.jl b/src/polars.jl index 902a4877..05957bc6 100644 --- a/src/polars.jl +++ b/src/polars.jl @@ -363,4 +363,3 @@ function read_aero_matrix(filepath::String) return matrix, alpha_values, delta_values end - diff --git a/src/wing_geometry.jl b/src/wing_geometry.jl index d7950894..506b91b4 100644 --- a/src/wing_geometry.jl +++ b/src/wing_geometry.jl @@ -1,4 +1,3 @@ - """ @with_kw mutable struct Section diff --git a/src/yaml_geometry.jl b/src/yaml_geometry.jl new file mode 100644 index 00000000..528b83c5 --- /dev/null +++ b/src/yaml_geometry.jl @@ -0,0 +1,227 @@ +@with_kw mutable struct AirfoilSettings + airfoil_id::Int64 + type::String + info_dict::Dict{String, Any} +end + +""" + YamlWing <: AbstractWing + +A wing model created from YAML configuration files with CSV polar data. + +## Core Features +- Wing geometry defined through YAML section coordinates +- Aerodynamic properties based on CSV polar data files +- Support for multiple airfoil types per wing +- Configurable panel distribution and geometry parameters + +## Notable Fields +- `n_panels::Int16`: Number of panels in aerodynamic mesh +- `n_groups::Int16`: Number of control groups +- `spanwise_distribution::PanelDistribution`: Panel distribution type +- `sections::Vector{Section}`: Wing cross-sections with aerodynamic data +- `airfoil_settings::Vector{AirfoilSettings}`: Airfoil configuration data +- `alpha_range::Vector{Float64}`: Angle of attack range for polars +- `reynolds::Float64`: Reynolds number for aerodynamic analysis + +See constructor `YamlWing(yaml_path; kwargs...)` for usage details. +""" +mutable struct YamlWing <: AbstractWing + n_panels::Int16 + n_groups::Int16 + spanwise_distribution::PanelDistribution + panel_props::PanelProperties + spanwise_direction::MVec3 + sections::Vector{Section} + refined_sections::Vector{Section} + remove_nan::Bool + + # Additional fields for YamlWing + airfoil_settings::Vector{AirfoilSettings} + alpha_range::Vector{Float64} + reynolds::Float64 + cache::Vector{PreallocationTools.LazyBufferCache{typeof(identity), typeof(identity)}} +end + +""" + load_polar_data(csv_file_path) + +Load polar data from CSV file at the given path. +Expected CSV format: columns named alpha, cl, cd, cm (case insensitive) + +Returns (aero_data, aero_model) tuple. +""" +function load_polar_data(csv_file_path::String) + if isempty(csv_file_path) || !isfile(csv_file_path) + @warn "Polar file not found or empty path: $csv_file_path. Using INVISCID model instead." + return nothing, INVISCID + end + + try + # Dynamically load CSV and DataFrames if not already loaded + if !isdefined(Main, :CSV) + @eval Main using CSV + end + if !isdefined(Main, :DataFrames) + @eval Main using DataFrames + end + + # Read CSV file + df = Main.DataFrame(Main.CSV.File(csv_file_path)) + + # Get column names and find required columns (case insensitive) + col_names = names(df) + col_names_lower = lowercase.(col_names) + + # Find required columns by matching lowercase names + alpha_col = findfirst(x -> x == "alpha", col_names_lower) + cl_col = findfirst(x -> x == "cl", col_names_lower) + cd_col = findfirst(x -> x == "cd", col_names_lower) + cm_col = findfirst(x -> x == "cm", col_names_lower) + + # Check if all required columns are found + if isnothing(alpha_col) || isnothing(cl_col) || isnothing(cd_col) || isnothing(cm_col) + missing_cols = String[] + isnothing(alpha_col) && push!(missing_cols, "alpha") + isnothing(cl_col) && push!(missing_cols, "cl") + isnothing(cd_col) && push!(missing_cols, "cd") + isnothing(cm_col) && push!(missing_cols, "cm") + @warn "Missing columns $missing_cols in $csv_file_path. Using INVISCID model instead." + return nothing, INVISCID + end + + # Extract data using actual column names + alpha_data = df[!, col_names[alpha_col]] + cl_data = df[!, col_names[cl_col]] + cd_data = df[!, col_names[cd_col]] + cm_data = df[!, col_names[cm_col]] + + # Create aero_data tuple + aero_data = (alpha_data, cl_data, cd_data, cm_data) + return aero_data, POLAR_VECTORS + + catch e + @warn "Error reading polar file $csv_file_path: $e. Using INVISCID model instead." + return nothing, INVISCID + end +end + +""" + YamlWing(yaml_path; kwargs...) + +Create a wing model from YAML configuration file with CSV polar data. + +This constructor builds a complete aerodynamic model by: +1. Loading wing geometry and airfoil configurations from YAML file +2. Loading aerodynamic polars from CSV files specified in the YAML +3. Creating wing sections with appropriate aerodynamic models +4. Setting up panel distribution and geometric properties + +# Arguments +- `yaml_path`: Path to YAML file containing wing geometry and airfoil specifications + +# Keyword Arguments +- `n_panels=20`: Number of aerodynamic panels across wingspan +- `n_groups=4`: Number of control groups +- `spanwise_distribution=LINEAR`: Panel distribution type +- `spanwise_direction=[0.0, 1.0, 0.0]`: Spanwise direction vector +- `remove_nan=true`: Interpolate NaN values in aerodynamic data +- `prn=true`: Print info messages during construction + +# Returns +A fully initialized `YamlWing` instance ready for aerodynamic simulation. + +# Example YAML format +```yaml +wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 10.0, 0.0, 1.0, 10.0, 0.0] + - [2, 0.0, -10.0, 0.0, 1.0, -10.0, 0.0] + +wing_airfoils: + alpha_range: [-10, 31, 0.5] + reynolds: 1e6 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "polars/1.csv"}] + - [2, polars, {csv_file_path: "polars/2.csv"}] +``` + +# Example +```julia +# Create a YAML-based wing from configuration file +wing = YamlWing( + "path/to/wing_config.yaml"; + n_panels=40, + n_groups=4 +) +``` +""" +function YamlWing( + yaml_path; + n_panels=20, + n_groups=4, + spanwise_distribution=LINEAR, + spanwise_direction=[0.0, 1.0, 0.0], + remove_nan=true, + prn=true +) + !(n_panels % n_groups == 0) && throw(ArgumentError("Number of panels should be divisible by number of groups")) + !isapprox(spanwise_direction, [0.0, 1.0, 0.0]) && throw(ArgumentError("Spanwise direction has to be [0.0, 1.0, 0.0], not $spanwise_direction")) + + prn && @info "Reading YAML wing configuration from $yaml_path" + + # Read and parse YAML file + yaml_data = YAML.load_file(yaml_path) + + # Parse airfoils and create CSV file mapping + airfoil_csv_map = Dict{Int64, String}() + airfoil_settings = AirfoilSettings[] + + for row in yaml_data["wing_airfoils"]["data"] + airfoil_dict = Dict(zip(yaml_data["wing_airfoils"]["headers"], row)) + airfoil_id, airfoil_type, info_dict = airfoil_dict["airfoil_id"], airfoil_dict["type"], airfoil_dict["info_dict"] + + push!(airfoil_settings, AirfoilSettings(airfoil_id, airfoil_type, info_dict)) + haskey(info_dict, "csv_file_path") && (airfoil_csv_map[airfoil_id] = info_dict["csv_file_path"]) + end + + # Parse sections and create wing sections + sections = Section[] + refined_sections = Section[] + + for row in yaml_data["wing_sections"]["data"] + section_dict = Dict(zip(yaml_data["wing_sections"]["headers"], row)) + airfoil_id = section_dict["airfoil_id"] + + # Get coordinates + le_coord = [section_dict["LE_x"], section_dict["LE_y"], section_dict["LE_z"]] + te_coord = [section_dict["TE_x"], section_dict["TE_y"], section_dict["TE_z"]] + + # Load polar data and create section + csv_file_path = get(airfoil_csv_map, airfoil_id, "") + if !isempty(csv_file_path) && !isabspath(csv_file_path) + # Make relative paths relative to YAML file directory + csv_file_path = joinpath(dirname(yaml_path), csv_file_path) + end + aero_data, aero_model = load_polar_data(csv_file_path) + + prn && println("Section airfoil_id $airfoil_id: Using $aero_model model") + + section = Section(le_coord, te_coord, aero_model, aero_data) + push!(sections, section) + push!(refined_sections, Section(le_coord, te_coord, aero_model, aero_data)) + end + + # Extract configuration + alpha_range = get(yaml_data["wing_airfoils"], "alpha_range", [-10.0, 31.0, 0.5]) + reynolds = get(yaml_data["wing_airfoils"], "reynolds", 1e6) + + # Create YamlWing + YamlWing( + n_panels, n_groups, spanwise_distribution, PanelProperties{n_panels}(), + MVec3(spanwise_direction), sections, refined_sections, remove_nan, + airfoil_settings, alpha_range, reynolds, [LazyBufferCache()] + ) +end From 420017de0f9433f323cd96ecc80af9aeb63aa653 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Mon, 4 Aug 2025 16:58:42 +0200 Subject: [PATCH 06/26] #185 V3 kite runs, but results are yet not accurate --- Project.toml | 2 +- data/TUDELFT_V3_KITE/2D_polars_CFD/1.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/10.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/11.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/12.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/13.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/14.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/15.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/16.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/17.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/18.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/19.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/2.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/3.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/4.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/5.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/6.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/7.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/8.csv | 71 ++++++ data/TUDELFT_V3_KITE/2D_polars_CFD/9.csv | 71 ++++++ data/TUDELFT_V3_KITE/geometry.yaml | 229 ++++++++++++++++++ .../V3_CL_CD_RANS_Lebesque_2024_Rey_300e4.csv | 0 data/TUDELFT_V3_KITE/vsm_settings.yaml | 36 +++ examples/V3_kite.jl | 92 +++++++ examples/menu.jl | 5 +- examples/pyramid_model.jl | 131 +++++++++- examples/ram_air_kite_v2.jl | 148 ----------- instantiate | 0 resolve | 0 src/yaml_geometry.jl | 134 ++++++---- 30 files changed, 1928 insertions(+), 198 deletions(-) create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/1.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/10.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/11.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/12.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/13.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/14.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/15.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/16.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/17.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/18.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/19.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/2.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/3.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/4.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/5.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/6.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/7.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/8.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/9.csv create mode 100644 data/TUDELFT_V3_KITE/geometry.yaml rename data/{TUDELFT_V3_LEI_KITE => TUDELFT_V3_KITE}/literature_results/V3_CL_CD_RANS_Lebesque_2024_Rey_300e4.csv (100%) create mode 100644 data/TUDELFT_V3_KITE/vsm_settings.yaml create mode 100644 examples/V3_kite.jl delete mode 100644 examples/ram_air_kite_v2.jl create mode 100644 instantiate create mode 100644 resolve diff --git a/Project.toml b/Project.toml index df34eed9..7487a232 100644 --- a/Project.toml +++ b/Project.toml @@ -75,4 +75,4 @@ Documenter = "e30172f5-a6a5-5a46-863b-614d45cd2de4" Test = "8dfed614-e22c-5e08-85e1-65c5234f0b40" [targets] -test = ["Test", "DataFrames", "CSV", "Documenter", "BenchmarkTools", "ControlPlots", "Aqua"] +test = ["Test", "DataFrames", "CSV", "Documenter", "BenchmarkTools", "ControlPlots", "Aqua"] \ No newline at end of file diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD/1.csv b/data/TUDELFT_V3_KITE/2D_polars_CFD/1.csv new file mode 100644 index 00000000..1b9cd368 --- /dev/null +++ b/data/TUDELFT_V3_KITE/2D_polars_CFD/1.csv @@ -0,0 +1,71 @@ +alpha,Cd,Cs,Cl,Cm +-10.0,0.0249065318608897,-3.434761974054366e-21,-1.0732064541182402,0.0054067639622245 +-9.5,0.0236873271741019,-3.285535810591269e-21,-1.0370727681402363,0.0058564293781756 +-9.0,0.0225262393305432,-3.1355323293482928e-21,-0.9992907398617008,0.0062213900212979 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--------------------------------------------------------------- + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [19, 0.10494809354160103, 4.110425010287237, 1.0206948819027293, 0.9322352740642089, 4.136759541813347, 1.0267698564834051] + - [18,-0.12594856150986303, 4.095312460948618, 1.131752674216157, 0.9480319715306028, 4.119176793915081, 1.1375068826415087] + - [17,-0.415204088177974, 4.058392218797549, 1.3527398161728057, 0.9806642670037444, 4.0661917809302714, 1.354784652851428] + - [16,-0.5839406178913704, 4.017404143963288, 1.573136130673558, 1.0133061573517872, 4.0126965083918655, 1.5718020624211284] + - [15,-0.6731255454312801, 3.9710648600916856, 1.792296994306359, 1.0459407519807051, 3.959304771307195, 1.788711553698102] + - [14,-0.7630010692513897, 3.808661454565653, 2.2116503076074623, 1.1148900094481449, 3.8099544198423287, 2.212462687618386] + - [13,-0.8034346573868656, 3.671721332477886, 2.3902080961084446, 1.1590484514963157, 3.676560321852442, 2.394355401152323] + - [12,-0.8426236438512831, 3.5037765531662273, 2.5431468790470166, 1.2069146554234733, 3.5081098865401383, 2.54813951074277] + - [11,-0.9107041725649544, 3.136094612354681, 2.798744478912709, 1.3282999037052468, 3.1343435230977734, 2.7965040693723457] + - [10,-0.9734084029764644, 2.799119438334862, 3.0942397365885954, 1.341651389866222, 2.7979060165852596, 3.0924012745521683] + - [9, -1.0012604181004636, 2.60606743950073, 3.2109156756433377, 1.3470535121521396, 2.607652208222479, 3.2140730423076005] + - [8, -1.0255704673876633, 2.3933957820040352, 3.2892227589446676, 1.3704766336634273, 2.3946575320852, 3.292717092764685] + - [7, -1.066808167099677, 1.9597511829533572, 3.398710571788576, 1.4286937460004634, 1.9587427796536303, 3.395858306351975] + - [6, -1.102721455861017, 1.5539231291222366, 3.587899390284646, 1.4218476587327253, 1.5529087742581646, 3.5847357425519175] + - [5, -1.1174483964012778, 1.3372547196154843, 3.6531307248857057, 1.4206278262933396, 1.337221665561774, 3.652962868560538] + - [4, -1.1290037004055944, 1.111273134975715, 3.672140965756021, 1.4350857915331694, 1.1111744842343718, 3.670881486234418] + - [3, -1.1448828836323988, 0.6642030404518473, 3.658203792543517, 1.4733964618305042, 0.6638228115665804, 3.653361447444984] + - [2, -1.1544229650457856, 0.22477286325409476, 3.739264150331224, 1.4484005139953104, 0.2247570459738744, 3.7390964622164637] + - [1, -1.1557911914860979, 0.0, 3.7549161879983592, 1.443146003226444, 0.0, 3.754972573823276] + - [2, -1.1544229650457856, -0.22477286325409476, 3.739264150331224, 1.4484005139953104, -0.2247570459738744, 3.7390964622164637] + - [3, -1.1448828836323988, -0.6642030404518473, 3.658203792543517, 1.4733964618305042, -0.6638228115665804, 3.653361447444984] + - [4, -1.1290037004055944, -1.111273134975715, 3.672140965756021, 1.4350857915331694, -1.1111744842343718, 3.670881486234418] + - [5, -1.1174483964012778, -1.3372547196154843, 3.6531307248857057, 1.4206278262933396, -1.337221665561774, 3.652962868560538] + - [6, -1.102721455861017, -1.5539231291222366, 3.587899390284646, 1.4218476587327253, -1.5529087742581646, 3.5847357425519175] + - [7, -1.066808167099677, -1.9597511829533572, 3.398710571788576, 1.4286937460004634, -1.9587427796536303, 3.395858306351975] + - [8, -1.0255704673876633, -2.3933957820040352, 3.2892227589446676, 1.3704766336634273, -2.3946575320852, 3.292717092764685] + - [9, -1.0012604181004636, -2.60606743950073, 3.2109156756433377, 1.3470535121521396, -2.607652208222479, 3.2140730423076005] + - [10,-0.9734084029764644, -2.799119438334862, 3.0942397365885954, 1.341651389866222, -2.7979060165852596, 3.0924012745521683] + - [11,-0.9107041725649544, -3.136094612354681, 2.798744478912709, 1.3282999037052468, -3.1343435230977734, 2.7965040693723457] + - [12,-0.8426236438512831, -3.5037765531662273, 2.5431468790470166, 1.2069146554234733, -3.5081098865401383, 2.54813951074277] + - [13,-0.8034346573868656, -3.671721332477886, 2.3902080961084446, 1.1590484514963157, -3.676560321852442, 2.394355401152323] + - [14,-0.7630010692513897, -3.808661454565653, 2.2116503076074623, 1.1148900094481449, -3.8099544198423287, 2.212462687618386] + - [15,-0.6731255454312801, -3.9710648600916856, 1.792296994306359, 1.0459407519807051, -3.959304771307195, 1.788711553698102] + - [16,-0.5839406178913704, -4.017404143963288, 1.573136130673558, 1.0133061573517872, -4.0126965083918655, 1.5718020624211284] + - [17,-0.415204088177974, -4.058392218797549, 1.3527398161728057, 0.9806642670037444, -4.0661917809302714, 1.354784652851428] + - [18,-0.12594856150986303, -4.095312460948618, 1.131752674216157, 0.9480319715306028, -4.119176793915081, 1.1375068826415087] + - [19, 0.10494809354160103, -4.110425010287237, 1.0206948819027293, 0.9322352740642089, -4.136759541813347, 1.0267698564834051] + +wing_airfoils: + # --------------------------------------------------------------- + # headers: + # - airfoil_id: integer, unique identifier for the airfoil + # - type: one of [neuralfoil, breukels_regression, masure_regression, polars] + # - info_dict: dictionary with parameters depending on 'type' + # + # info_dict fields by type: + # - breukels_regression: + # t: Tube diameter non-dimensionalized by chord (required) + # kappa: Maximum camber height/magnitude, non-dimensionalized by chord (required) + # - neuralfoil: + # dat_file_path: Path to airfoil .dat file (x, y columns) + # model_size: NeuralFoil model size (e.g., "xxxlarge") + # xtr_lower: Lower transition location (0=forced, 1=free) + # xtr_upper: Upper transition location + # n_crit: Critical amplification factor (see guidelines below) + # n_crit guidelines: + # Sailplane: 12–14 + # Motorglider: 11–13 + # Clean wind tunnel: 10–12 + # Average wind tunnel: 9 (standard "e^9 method") + # Dirty wind tunnel: 4–8 + # - polars: + # csv_file_path: Path to polar CSV file (columns: alpha [rad], cl, cd, cm) + # - masure_regression: + # t, eta, kappa, delta, lamba, phi: Regression parameters + # - inviscid: + # no further data is required + # --------------------------------------------------------------- + alpha_range: [-10, 31, 0.5] # [deg], in this range the polars are calculated + reynolds: !!float 1e6 # Reynolds number + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "2D_polars_CFD/1.csv"}] + - [2, polars, {csv_file_path: "2D_polars_CFD/2.csv"}] + - [3, polars, {csv_file_path: "2D_polars_CFD/3.csv"}] + - [4, polars, {csv_file_path: "2D_polars_CFD/4.csv"}] + - [5, polars, {csv_file_path: "2D_polars_CFD/5.csv"}] + - [6, polars, {csv_file_path: "2D_polars_CFD/6.csv"}] + - [7, polars, {csv_file_path: "2D_polars_CFD/7.csv"}] + - [8, polars, {csv_file_path: "2D_polars_CFD/8.csv"}] + - [9, polars, {csv_file_path: "2D_polars_CFD/9.csv"}] + - [10, polars, {csv_file_path: "2D_polars_CFD/10.csv"}] + - [11, polars, {csv_file_path: "2D_polars_CFD/11.csv"}] + - [12, polars, {csv_file_path: "2D_polars_CFD/12.csv"}] + - [13, polars, {csv_file_path: "2D_polars_CFD/13.csv"}] + - [14, polars, {csv_file_path: "2D_polars_CFD/14.csv"}] + - [15, polars, {csv_file_path: "2D_polars_CFD/15.csv"}] + - [16, polars, {csv_file_path: "2D_polars_CFD/16.csv"}] + - [17, polars, {csv_file_path: "2D_polars_CFD/17.csv"}] + - [18, polars, {csv_file_path: "2D_polars_CFD/18.csv"}] + - [19, polars, {csv_file_path: "2D_polars_CFD/19.csv"}] + + + +bridle_nodes: + # --------------------------------------------------------------- + # headers: + # - id: integer, unique identifier for the node + # - x: x-coordinate [m] + # - y: y-coordinate [m] + # - z: z-coordinate [m] + # - type: node type, either 'knot' or 'pulley' + # --------------------------------------------------------------- + headers: [id, x, y, z, type] + data: + - [21, -0.67653494, 2.10580567, 7.08413599, knot] + - [22, -0.79196791, 1.01882151, 7.57069579, knot] + - [23, -0.79196791, -1.01882151, 7.57069579, knot] + - [24, -0.67653494, -2.10580567, 7.08413599, knot] + - [25, -0.46444477, 0.77505128, 4.23316161, knot] + - [26, -0.46444477, -0.77505128, 4.23316161, knot] + - [27, 0.54344694, 1.57655435, 5.91086207, knot] + - [28, 0.62960591, 0.92728966, 6.64639402, knot] + - [29, 0.62960591, -0.92728966, 6.64639402, knot] + - [30, 0.54344694, -1.57655435, 5.91086207, knot] + - [31, 0.39092886, 0.71221536, 4.26118728, knot] + - [32, 0.39092886, -0.71221536, 4.26118728, knot] + - [33, 0.30679124, 0.49235914, 3.39885672, pulley] + - [34, 0.28625931, 0.0, 3.19030736, knot] + - [35, 0.30679124, -0.49235914, 3.39885672, pulley] + - [36, 0.13269336, 0.23394851, 1.48060245, knot] + - [37, 0.13269336, -0.23394851, 1.48060245, knot] + +bridle_lines: + # --------------------------------------------------------------- + # headers: + # - name: string, line name + # - rest_length: measured rest length [m] + # - diameter: line diameter [m] + # - material: string, material type (e.g., dyneema) + # - density: material density [kg/m^3] + # --------------------------------------------------------------- + headers: [name, rest_length, diameter, material, density] + data: + # front lines + - [a6, 11.790, 0.002, dyneema,970] + - [A5, 2.870, 0.002, dyneema,970] + - [A3, 3.450, 0.002, dyneema,970] + - [A2, 3.500, 0.002, dyneema,970] + - [A1, 3.690, 0.002, dyneema,970] + - [AII, 3.250, 0.002, dyneema,970] + - [AI, 3.620, 0.002, dyneema,970] + - [amain, 3.910, 0.002, dyneema,970] + # rear lines + - [br1, 4.410, 0.002, dyneema,970] + - [br2, 4.170, 0.002, dyneema,970] + - [br3, 4.140, 0.002, dyneema,970] + - [br5, 3.580, 0.002, dyneema,970] + - [br6, 13.560, 0.002, dyneema,970] + - [BRI, 2.360, 0.002, dyneema,970] + - [BRII, 2.080, 0.002, dyneema,970] + - [BR-main-1, .700, 0.002, dyneema,970] + - [M-line, 2.410, 0.002, dyneema,970] + # - [S, 1.730, 0.002, dyneema,970] # measured + # - [Power Tape, 3.330, 0.002, polyester] # measured + - [Steering Tape, 1.530, 0.002, dyneema,970] # trying 0.2m smalller + - [Power Tape, 2.900, 0.002, dyneema,970] # trying 0.2m smaller + +bridle_connections: + # --------------------------------------------------------------- + # headers: + # - name: string, line name + # - ci: integer, node id (start) + # - cj: integer, node id (end) + # - ck: integer, third node id (only for pulleys, else omitted or 0) + # --------------------------------------------------------------- + headers: [name, ci, cj, ck] + data: + # front lines + - [a6,1,25,33] #e.g. this is a pulley + - [A5,3,21] + - [A3,5,21] + - [A2,7,22] + - [A1,9,22] + - [A1,11,23] + - [A2,13,23] + - [A3,15,24] + - [A5,17,24] + - [a6,19,26,35] + - [AII,21,25] + - [AI,22,25] + - [AI,23,26] + - [AII,24,26] + - [amain,25,0] + - [amain,26,0] + # rear lines + - [a6,1,33,25] + - [br6,2,33,36] + - [br6,2,36,33] + - [br5,4,27] + - [br3,6,27] + - [br2,8,28] + - [br1,10,28] + - [br1,12,29] + - [br2,14,29] + - [br3,16,30] + - [br5,18,30] + - [a6,19,35,26] + - [br6,20,35,37] + - [br6,20,37,35] + - [BRII,27,31] + - [BRI,28,31] + - [BRI,29,32] + - [BRII,30,32] + - [BR-main-1,31,33] + - [BR-main-1,32,35] + - [M-line,33,36,34] + - [M-line,33,34,36] + - [M-line,35,34,37] + - [M-line,35,37,34] + - [Steering Tape,36,0] + - [Power Tape,34,0] + - [Steering Tape,37,0] + + + diff --git a/data/TUDELFT_V3_LEI_KITE/literature_results/V3_CL_CD_RANS_Lebesque_2024_Rey_300e4.csv b/data/TUDELFT_V3_KITE/literature_results/V3_CL_CD_RANS_Lebesque_2024_Rey_300e4.csv similarity index 100% rename from data/TUDELFT_V3_LEI_KITE/literature_results/V3_CL_CD_RANS_Lebesque_2024_Rey_300e4.csv rename to data/TUDELFT_V3_KITE/literature_results/V3_CL_CD_RANS_Lebesque_2024_Rey_300e4.csv diff --git a/data/TUDELFT_V3_KITE/vsm_settings.yaml b/data/TUDELFT_V3_KITE/vsm_settings.yaml new file mode 100644 index 00000000..5ae66dc9 --- /dev/null +++ b/data/TUDELFT_V3_KITE/vsm_settings.yaml @@ -0,0 +1,36 @@ +Model: + VSM: Vortex Step Method + LLT: Lifting Line Theory +PanelDistribution: + LINEAR: Linear distribution + COSINE: Cosine distribution + COSINE_VAN_GARREL: van Garrel cosine distribution + SPLIT_PROVIDED: Split provided sections + UNCHANGED: Keep original sections +InitialGammaDistribution: + ELLIPTIC: Elliptic distribution + ZEROS: Constant distribution + +wings: + - name: main_wing + n_panels: 40 + n_groups: 40 + spanwise_panel_distribution: LINEAR + spanwise_direction: [0.0, 1.0, 0.0] + remove_nan: true +solver_settings: + n_panels: 40 + n_groups: 40 + aerodynamic_model_type: VSM + density: 1.225 # air density [kg/m³] + max_iterations: 1500 + rtol: 1e-5 # relative error [-] + tol_reference_error: 0.001 + relaxation_factor: 0.03 # relaxation factor for convergence + artificial_damping: false # whether to apply artificial damping + k2: 0.1 # artificial damping parameter + k4: 0.0 # artificial damping parameter + type_initial_gamma_distribution: ELLIPTIC + core_radius_fraction: 1e-20 + mu: 1.81e-5 # dynamic viscosity [N·s/m²] + calc_only_f_and_gamma: false # whether to only output f and gamma diff --git a/examples/V3_kite.jl b/examples/V3_kite.jl new file mode 100644 index 00000000..670d41bf --- /dev/null +++ b/examples/V3_kite.jl @@ -0,0 +1,92 @@ +using LinearAlgebra +using VortexStepMethod +using ControlPlots + +# --- User-specified parameters --- +wind_speed = 10.0 # [m/s] +angle_of_attack_deg = 5.0 # [deg] +sideslip_deg = 0.0 +yaw_rate = 0.0 # [rad/s] (not used in static analysis) +air_density = 1.225 # [kg/m^3] Air density at sea level +project_dir = dirname(dirname(pathof(VortexStepMethod))) # Go up one level from src to project root +yaml_geometry_path = joinpath(project_dir, "data", "TUDELFT_V3_KITE", "geometry.yaml") + +println("=== Static Aerodynamic Analysis (VSM) ===") +println("Wind speed: $wind_speed m/s") +println("Angle of attack: $angle_of_attack_deg deg") +println("Sideslip: $sideslip_deg deg") + +# Create wing geometry from YAML (following RamAirWing pattern) +wing = YamlWing(yaml_geometry_path; n_panels=20, spanwise_distribution=LINEAR) +body_aero = BodyAerodynamics([wing]) + +# --- Set apparent wind vector in body axes --- +α = deg2rad(angle_of_attack_deg) +β = deg2rad(sideslip_deg) +va = wind_speed * [ + cos(α)*cos(β), # X_b (forward) + sin(β), # Y_b (right) + sin(α)*cos(β) # Z_b (down) +] +set_va!(body_aero, va) + +# --- Create and run VSM solver --- +solver = Solver(body_aero; + aerodynamic_model_type=VSM, + is_with_artificial_damping=false, + rtol=1e-5, + solver_type=NONLIN +) +results = VortexStepMethod.solve(solver, body_aero; log=true) + +# Using plotting modules, to create more comprehensive plots +PLOT = true +USE_TEX = false + + +# Plotting geometry +PLOT && plot_geometry( + body_aero, + ""; + data_type=".svg", + save_path="", + is_save=false, + is_show=true, + view_elevation=15, + view_azimuth=-120, + use_tex=USE_TEX +) + +# Plotting polars +PLOT && plot_polars( + [solver], + [body_aero], + ["V3 Kite"], + angle_range=range(0, 25, length=20), + angle_type="angle_of_attack", + angle_of_attack=5, + side_slip=0, + v_a=10, + title="$(wing.n_panels)_distribution_$(wing.spanwise_distribution)", + data_type=".pdf", + is_save=false, + is_show=true, + use_tex=USE_TEX +) + +# Plotting spanwise distributions +body_y_coordinates = [panel.aero_center[2] for panel in body_aero.panels] + +PLOT && plot_distribution( + [body_y_coordinates], + [results], + ["VSM"]; + title="CAD_spanwise_distributions_alpha_$(round(angle_of_attack_deg, digits=1))_delta_$(round(sideslip_deg, digits=1))_yaw_$(round(yaw_rate, digits=1))_v_a_$(round(wind_speed, digits=1))", + data_type=".pdf", + is_save=false, + is_show=true, + use_tex=USE_TEX +) + + +nothing \ No newline at end of file diff --git a/examples/menu.jl b/examples/menu.jl index 2160ca85..4454ccee 100644 --- a/examples/menu.jl +++ b/examples/menu.jl @@ -10,8 +10,9 @@ using REPL.TerminalMenus url = "https://opensourceawe.github.io/VortexStepMethod.jl/dev" options = [ - "pyramid_model = include(\"pyramid_model.jl\")", - "rectangular_wing = include(\"rectangular_wing.jl\")", + "V3_kite = include(\"V3_kite.jl\")", + "pyramid_model = include(\"pyramid_model.jl\")", + "rectangular_wing = include(\"rectangular_wing.jl\")", "ram_air_kite = include(\"ram_air_kite.jl\")", "stall_model = include(\"stall_model.jl\")", "bench = include(\"bench.jl\")", diff --git a/examples/pyramid_model.jl b/examples/pyramid_model.jl index fa48f71e..dccd5c56 100644 --- a/examples/pyramid_model.jl +++ b/examples/pyramid_model.jl @@ -2,17 +2,108 @@ using LinearAlgebra using VortexStepMethod using ControlPlots -# settings +# --- User-specified parameters --- +wind_speed = 10.0 # [m/s] +angle_of_attack_deg = 5.0 # [deg] +sideslip_deg = 0.0 +yaw_rate = 0.0 # [rad/s] (not used in static analysis) +air_density = 1.225 # [kg/m^3] Air density at sea level project_dir = dirname(dirname(pathof(VortexStepMethod))) # Go up one level from src to project root yaml_geometry_path = joinpath(project_dir, "data", "pyramid_model", "geometry.yaml") +println("=== Static Aerodynamic Analysis (VSM) ===") +println("Wind speed: $wind_speed m/s") +println("Angle of attack: $angle_of_attack_deg deg") +println("Sideslip: $sideslip_deg deg") + # Create wing geometry from YAML (following RamAirWing pattern) wing = YamlWing(yaml_geometry_path; n_panels=20, spanwise_distribution=LINEAR) body_aero = BodyAerodynamics([wing]) -# Plotting Geometry +# --- Set apparent wind vector in body axes --- +α = deg2rad(angle_of_attack_deg) +β = deg2rad(sideslip_deg) +va = wind_speed * [ + cos(α)*cos(β), # X_b (forward) + sin(β), # Y_b (right) + sin(α)*cos(β) # Z_b (down) +] +set_va!(body_aero, va) + +# --- Create and run VSM solver --- +solver = Solver(body_aero; + aerodynamic_model_type=VSM, + is_with_artificial_damping=false, + rtol=1e-5, + solver_type=NONLIN +) + +# One can run the solver seperately, given back a Dict{String, Any} +solver = Solver(body_aero; density=air_density) +solve!(solver, body_aero) +forces = solver.sol.force +println("\nType of solver: ", typeof(solver), " Type of forces: ", typeof(forces)) + +# Better to use the VortexStepMethod.solve method, returns a dictionary with the results +results = VortexStepMethod.solve(solver, body_aero; log=true) +println("Type of results: ", typeof(results)) + + +# --- Run over an alpha sweep --- +# using Plots # Add this at the top if you want to plot +alphas = 1:10 +f_xs = Float64[] # Fx over alpha sweep +f_ys = Float64[] # Fy over alpha sweep +f_zs = Float64[] # Fz over alpha sweep +m_xs = Float64[] # Mx over alpha sweep +m_ys = Float64[] # My over alpha sweep +m_zs = Float64[] # Mz over alpha sweep + +for alpha in alphas + local_α = deg2rad(alpha) + local_β = deg2rad(sideslip_deg) + local_va = wind_speed * [ + cos(local_α)*cos(local_β), + sin(local_β), + sin(local_α)*cos(local_β) + ] + set_va!(body_aero, local_va) + + solve!(solver, body_aero) + results_i = VortexStepMethod.solve(solver, body_aero; log=true) + + push!(f_xs, results_i["Fx"]) + push!(f_ys, results_i["Fy"]) + push!(f_zs, results_i["Fz"]) + push!(m_xs, results_i["Mx"]) + push!(m_ys, results_i["My"]) + push!(m_zs, results_i["Mz"]) + +end + + +# --- Plot results: true multi-row plotx style as in simple_lin_model.jl --- +p = plotx( + alphas, + f_xs, + f_ys, + f_zs, + m_xs, + m_ys, + m_zs; + ylabels=["Fx [N]", "Fy [N]", "Fz [N]", "Mx [Nm]", "My [Nm]", "Mz [Nm]"], + xlabel="alpha [deg]", + fig="Aerodynamic Forces and Moments" +) +display(p) + + +# Using plotting modules, to create more comprehensive plots PLOT = true USE_TEX = false + + +# Plotting geometry PLOT && plot_geometry( body_aero, ""; @@ -23,4 +114,38 @@ PLOT && plot_geometry( view_elevation=15, view_azimuth=-120, use_tex=USE_TEX -) \ No newline at end of file +) + +# Plotting polars +PLOT && plot_polars( + [solver], + [body_aero], + ["VSM from Ram Air Kite OBJ and DAT file"], + angle_range=range(0, 20, length=20), + angle_type="angle_of_attack", + angle_of_attack=5, + side_slip=0, + v_a=10, + title="pyramid $(wing.n_panels)_distribution_$(wing.spanwise_distribution)", + data_type=".pdf", + is_save=false, + is_show=true, + use_tex=USE_TEX +) + +# Plotting spanwise distributions +body_y_coordinates = [panel.aero_center[2] for panel in body_aero.panels] + +PLOT && plot_distribution( + [body_y_coordinates], + [results], + ["VSM"]; + title="CAD_spanwise_distributions_alpha_$(round(angle_of_attack_deg, digits=1))_delta_$(round(sideslip_deg, digits=1))_yaw_$(round(yaw_rate, digits=1))_v_a_$(round(wind_speed, digits=1))", + data_type=".pdf", + is_save=false, + is_show=true, + use_tex=USE_TEX +) + + +nothing \ No newline at end of file diff --git a/examples/ram_air_kite_v2.jl b/examples/ram_air_kite_v2.jl deleted file mode 100644 index d599a2d6..00000000 --- a/examples/ram_air_kite_v2.jl +++ /dev/null @@ -1,148 +0,0 @@ -using VortexStepMethod,LinearAlgebra -using ControlPlots # Use plotx instead of Plots - -# --- User-specified parameters --- -wind_speed = 10.0 # [m/s] -angle_of_attack_deg = 5.0 # [deg] -sideslip_deg = 0.0 -yaw_rate = 0.0 # [rad/s] (not used in static analysis) -air_density = 1.225 # [kg/m^3] Air density at sea level - -println("=== Static Aerodynamic Analysis (VSM) ===") -println("Wind speed: $wind_speed m/s") -println("Angle of attack: $angle_of_attack_deg deg") -println("Sideslip: $sideslip_deg deg") - -# --- Setup kite and aero model --- -ram_wing = RamAirWing("data/ram_air_kite_body.obj", "data/ram_air_kite_foil.dat"; align_to_principal=true) -body_aero = BodyAerodynamics([ram_wing]) - -# --- Set apparent wind vector in body axes --- -α = deg2rad(angle_of_attack_deg) -β = deg2rad(sideslip_deg) -va = wind_speed * [ - cos(α)*cos(β), # X_b (forward) - sin(β), # Y_b (right) - sin(α)*cos(β) # Z_b (down) -] -set_va!(body_aero, va) - -# --- Create and run VSM solver --- -solver = Solver(body_aero; - aerodynamic_model_type=VSM, - is_with_artificial_damping=false, - rtol=1e-5, - solver_type=NONLIN -) - -# One can run the solver seperately, given back a Dict{String, Any} -solver = Solver(body_aero; density=air_density) -solve!(solver, body_aero) -forces = solver.sol.force -println("\nType of solver: ", typeof(solver), " Type of forces: ", typeof(forces)) - -# Better to use the VortexStepMethod.solve method, returns a dictionary with the results -results = VortexStepMethod.solve(solver, body_aero; log=true) -println("Type of results: ", typeof(results)) - - -# --- Run over an alpha sweep --- -# using Plots # Add this at the top if you want to plot -alphas = 1:10 -f_xs = Float64[] # Fx over alpha sweep -f_ys = Float64[] # Fy over alpha sweep -f_zs = Float64[] # Fz over alpha sweep -m_xs = Float64[] # Mx over alpha sweep -m_ys = Float64[] # My over alpha sweep -m_zs = Float64[] # Mz over alpha sweep - -for alpha in alphas - local_α = deg2rad(alpha) - local_β = deg2rad(sideslip_deg) - local_va = wind_speed * [ - cos(local_α)*cos(local_β), - sin(local_β), - sin(local_α)*cos(local_β) - ] - set_va!(body_aero, local_va) - - solve!(solver, body_aero) - results_i = VortexStepMethod.solve(solver, body_aero; log=true) - - push!(f_xs, results_i["Fx"]) - push!(f_ys, results_i["Fy"]) - push!(f_zs, results_i["Fz"]) - push!(m_xs, results_i["Mx"]) - push!(m_ys, results_i["My"]) - push!(m_zs, results_i["Mz"]) - -end - - -# --- Plot results: true multi-row plotx style as in simple_lin_model.jl --- -p = plotx( - alphas, - f_xs, - f_ys, - f_zs, - m_xs, - m_ys, - m_zs; - ylabels=["Fx [N]", "Fy [N]", "Fz [N]", "Mx [Nm]", "My [Nm]", "Mz [Nm]"], - xlabel="alpha [deg]", - fig="Aerodynamic Forces and Moments" -) -display(p) - - -# Using plotting modules, to create more comprehensive plots -PLOT = true -USE_TEX = false - - -# Plotting geometry -PLOT && plot_geometry( - body_aero, - ""; - data_type=".svg", - save_path="", - is_save=false, - is_show=true, - view_elevation=15, - view_azimuth=-120, - use_tex=USE_TEX -) - -# Plotting polars -PLOT && plot_polars( - [solver], - [body_aero], - ["VSM from Ram Air Kite OBJ and DAT file"], - angle_range=range(0, 20, length=20), - angle_type="angle_of_attack", - angle_of_attack=5, - side_slip=0, - v_a=10, - title="ram_kite_panels_$(ram_wing.n_panels)_distribution_$(ram_wing.spanwise_distribution)", - data_type=".pdf", - is_save=false, - is_show=true, - use_tex=USE_TEX -) - -# Plotting spanwise distributions -body_y_coordinates = [panel.aero_center[2] for panel in body_aero.panels] - -PLOT && plot_distribution( - [body_y_coordinates], - [results], - ["VSM"]; - title="CAD_spanwise_distributions_alpha_$(round(angle_of_attack_deg, digits=1))_delta_$(round(sideslip_deg, digits=1))_yaw_$(round(yaw_rate, digits=1))_v_a_$(round(wind_speed, digits=1))", - data_type=".pdf", - is_save=false, - is_show=true, - use_tex=USE_TEX -) - - -nothing \ No newline at end of file diff --git a/instantiate b/instantiate new file mode 100644 index 00000000..e69de29b diff --git a/resolve b/resolve new file mode 100644 index 00000000..e69de29b diff --git a/src/yaml_geometry.jl b/src/yaml_geometry.jl index 528b83c5..eefff405 100644 --- a/src/yaml_geometry.jl +++ b/src/yaml_geometry.jl @@ -43,69 +43,115 @@ mutable struct YamlWing <: AbstractWing cache::Vector{PreallocationTools.LazyBufferCache{typeof(identity), typeof(identity)}} end +# """ +# load_polar_data(csv_file_path) + +# Load polar data from CSV file at the given path. +# Expected CSV format: columns named alpha, cl, cd, cm (case insensitive) + +# Returns (aero_data, aero_model) tuple. +# """ +# function load_polar_data(csv_file_path::String) +# if isempty(csv_file_path) || !isfile(csv_file_path) +# @warn "Polar file not found or empty path: $csv_file_path. Using INVISCID model instead." +# return nothing, INVISCID +# end + +# try +# # Read the file and get headers +# file_content = readdlm(csv_file_path, ',') + +# # Extract headers (first row) and data (remaining rows) +# headers = String.(file_content[1, :]) +# data = file_content[2:end, :] +# # Get column names and find required columns (case insensitive) +# col_names_lower = lowercase.(headers) + +# # Find required columns by matching lowercase names +# alpha_col = findfirst(x -> x == "alpha", col_names_lower) +# cl_col = findfirst(x -> x == "cl", col_names_lower) +# cd_col = findfirst(x -> x == "cd", col_names_lower) +# cm_col = findfirst(x -> x == "cm", col_names_lower) + +# # Check if all required columns are found +# if isnothing(alpha_col) || isnothing(cl_col) || isnothing(cd_col) || isnothing(cm_col) +# missing_cols = String[] +# isnothing(alpha_col) && push!(missing_cols, "alpha") +# isnothing(cl_col) && push!(missing_cols, "cl") +# isnothing(cd_col) && push!(missing_cols, "cd") +# isnothing(cm_col) && push!(missing_cols, "cm") +# @warn "Missing columns $missing_cols in $csv_file_path. Using INVISCID model instead." +# return nothing, INVISCID +# end + +# # Extract data using column indices and convert to Float64 +# alpha_data = Float64.(data[:, alpha_col]) +# cl_data = Float64.(data[:, cl_col]) +# cd_data = Float64.(data[:, cd_col]) +# cm_data = Float64.(data[:, cm_col]) + +# # Create aero_data tuple +# aero_data = (alpha_data, cl_data, cd_data, cm_data) +# return aero_data, POLAR_VECTORS + +# catch e +# @warn "Error reading polar file $csv_file_path: $e. Using INVISCID model instead." +# return nothing, INVISCID +# end +# end """ load_polar_data(csv_file_path) -Load polar data from CSV file at the given path. -Expected CSV format: columns named alpha, cl, cd, cm (case insensitive) +Load polar data from a CSV file using only `readlines`. +Expected format: header row and columns alpha, cl, cd, cm (case-insensitive, order arbitrary). -Returns (aero_data, aero_model) tuple. +Returns (aero_data, POLAR_VECTORS) or (nothing, INVISCID) if missing/invalid. """ function load_polar_data(csv_file_path::String) if isempty(csv_file_path) || !isfile(csv_file_path) @warn "Polar file not found or empty path: $csv_file_path. Using INVISCID model instead." return nothing, INVISCID end - try - # Dynamically load CSV and DataFrames if not already loaded - if !isdefined(Main, :CSV) - @eval Main using CSV - end - if !isdefined(Main, :DataFrames) - @eval Main using DataFrames - end - - # Read CSV file - df = Main.DataFrame(Main.CSV.File(csv_file_path)) - - # Get column names and find required columns (case insensitive) - col_names = names(df) - col_names_lower = lowercase.(col_names) - - # Find required columns by matching lowercase names - alpha_col = findfirst(x -> x == "alpha", col_names_lower) - cl_col = findfirst(x -> x == "cl", col_names_lower) - cd_col = findfirst(x -> x == "cd", col_names_lower) - cm_col = findfirst(x -> x == "cm", col_names_lower) - - # Check if all required columns are found - if isnothing(alpha_col) || isnothing(cl_col) || isnothing(cd_col) || isnothing(cm_col) - missing_cols = String[] - isnothing(alpha_col) && push!(missing_cols, "alpha") - isnothing(cl_col) && push!(missing_cols, "cl") - isnothing(cd_col) && push!(missing_cols, "cd") - isnothing(cm_col) && push!(missing_cols, "cm") - @warn "Missing columns $missing_cols in $csv_file_path. Using INVISCID model instead." + lines = readlines(csv_file_path) + isempty(lines) && throw(ArgumentError("File is empty")) + header = lowercase.(split(strip(lines[1]), ',')) + + # Create a mapping from column name to index (1-based for Julia arrays) + col_map = Dict(name => i for (i, name) in enumerate(header)) + required = ["alpha", "cl", "cd", "cm"] + missing = filter(x -> !haskey(col_map, x), required) + if !isempty(missing) + @warn "Missing columns $missing in $csv_file_path. Using INVISCID model instead." return nothing, INVISCID end - - # Extract data using actual column names - alpha_data = df[!, col_names[alpha_col]] - cl_data = df[!, col_names[cl_col]] - cd_data = df[!, col_names[cd_col]] - cm_data = df[!, col_names[cm_col]] - - # Create aero_data tuple - aero_data = (alpha_data, cl_data, cd_data, cm_data) - return aero_data, POLAR_VECTORS - + + # Preallocate arrays + n = length(lines) - 1 + alpha = Vector{Float64}(undef, n) + cl = Vector{Float64}(undef, n) + cd = Vector{Float64}(undef, n) + cm = Vector{Float64}(undef, n) + + # Converting to radians + alpha = deg2rad.(alpha) + + # Read each data line + for (i, line) in enumerate(lines[2:end]) + fields = split(strip(line), ',') + alpha[i] = parse(Float64, fields[col_map["alpha"]]) + cl[i] = parse(Float64, fields[col_map["cl"]]) + cd[i] = parse(Float64, fields[col_map["cd"]]) + cm[i] = parse(Float64, fields[col_map["cm"]]) + end + return (alpha, cl, cd, cm), POLAR_VECTORS catch e @warn "Error reading polar file $csv_file_path: $e. Using INVISCID model instead." return nothing, INVISCID end end + """ YamlWing(yaml_path; kwargs...) From 60ef204538e07ed77a8e97d5b25297244e998af8 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Tue, 5 Aug 2025 08:54:45 +0200 Subject: [PATCH 07/26] #185 setting standard printing to false, adding literature results for V3 Kite, and adjusting plotting script to handle arbitrary column sorting of literature input --- ...Rey_10e5_Poland2025_alpha_sweep_beta_0.csv | 9 ++ ...Poland2025_alpha_sweep_beta_0_NoStruts.csv | 19 +++ ..._Rey_5e5_Poland2025_alpha_sweep_beta_0.csv | 39 ++++++ .../V3_CL_CD_RANS_Lebesque_2024_Rey_300e4.csv | 19 --- ...l_Re_5e5_Poland2025_alpha_sweep_beta_0.csv | 18 +++ examples/V3_kite.jl | 112 ++++++++++-------- src/plotting.jl | 20 +++- src/yaml_geometry.jl | 2 +- 8 files changed, 164 insertions(+), 74 deletions(-) create mode 100644 data/TUDELFT_V3_KITE/literature_results/CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv create mode 100644 data/TUDELFT_V3_KITE/literature_results/CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv create mode 100644 data/TUDELFT_V3_KITE/literature_results/Python_VSM_Rey_5e5_Poland2025_alpha_sweep_beta_0.csv delete mode 100644 data/TUDELFT_V3_KITE/literature_results/V3_CL_CD_RANS_Lebesque_2024_Rey_300e4.csv create mode 100644 data/TUDELFT_V3_KITE/literature_results/WindTunnel_Re_5e5_Poland2025_alpha_sweep_beta_0.csv diff --git a/data/TUDELFT_V3_KITE/literature_results/CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv b/data/TUDELFT_V3_KITE/literature_results/CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv new file mode 100644 index 00000000..f619300f --- /dev/null +++ b/data/TUDELFT_V3_KITE/literature_results/CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv @@ -0,0 +1,9 @@ +alpha,beta,CL,CD,CS,CMy +1.02,0,0.2278625272194466,0.0490919571607997,-0.028991478200473,-0.0971304889257096 +4.02,0,0.4610104802890269,0.0516566817024969,-0.06116291297791359,-0.177995425157634 +7.02,0,0.6748642166054709,0.0643789856608573,-0.09170612013580448,-0.2399628564061313 +10.02,0,0.8685945393341531,0.0841781647387978,-0.12014981939630065,-0.2873743657009342 +13.02,0,1.042518829707241,0.1099699784207837,-0.14632493718395287,-0.3234126609849657 +15.02,0,1.147266423064987,0.1293063892392999,-0.16260131332214534,-0.3422906659660041 +17.02,0,1.248363457881334,0.1505397278170317,-0.17819835351371366,-0.3593648645427019 +19.02,0,1.340909392696446,0.172443901716702,-0.19275273990602687,-0.3729793258363525 diff --git a/data/TUDELFT_V3_KITE/literature_results/CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv b/data/TUDELFT_V3_KITE/literature_results/CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv new file mode 100644 index 00000000..eed0a9c8 --- /dev/null +++ b/data/TUDELFT_V3_KITE/literature_results/CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv @@ -0,0 +1,19 @@ +CL,CD,alpha,CS +-0.133333333,0.0728,-3.98,0 +-0.066666667,0.0672,-2.98,0 +0.073015873,0.0552,-0.98,0 +0.225396825,0.051,1.02,0 +0.384126984,0.052,3.02,0 +0.46031746,0.0536,4.02,0 +0.536507937,0.06,5.02,0 +0.673015873,0.07,7.02,0 +0.803174603,0.075,9.02,0 +0.873015873,0.085,10.02,0 +0.93015873,0.09,11.02,0 +1.041269841,0.115,13.02,0 +1.146031746,0.135,15.02,0 +1.24,0.151,17.02,0 +1.342857143,0.171,19.02,0 +0.88,0.31,21.02,0 +0.91,0.34,23.02,0 +0.93,0.38,25.02,0 diff --git a/data/TUDELFT_V3_KITE/literature_results/Python_VSM_Rey_5e5_Poland2025_alpha_sweep_beta_0.csv b/data/TUDELFT_V3_KITE/literature_results/Python_VSM_Rey_5e5_Poland2025_alpha_sweep_beta_0.csv new file mode 100644 index 00000000..65726bed --- /dev/null +++ b/data/TUDELFT_V3_KITE/literature_results/Python_VSM_Rey_5e5_Poland2025_alpha_sweep_beta_0.csv @@ -0,0 +1,39 @@ +alpha,CL,CD,CL/CD,CS +-12.0,-0.2382871512913027,0.10555351086138359,-2.2575009523295666,8.493387378390686e-14 +-11.0,-0.23078413996904473,0.10186112684362705,-2.265674326608765,6.616874649497016e-14 +-10.0,-0.22230140038021914,0.09806363640487119,-2.266909616347621,4.373272668096159e-14 +-9.0,-0.21585315982172304,0.0931590398953698,-2.317039334713575,2.739682786368477e-14 +-8.0,-0.20625706590216833,0.08814998331707347,-2.339842370250558,1.1046588689401156e-14 +-7.0,-0.1998343140258721,0.08290261953105998,-2.410470442987666,-2.389661935808156e-14 +-6.0,-0.18199775713691974,0.07765158375393942,-2.343773923705537,-3.872611350474041e-14 +-5.0,-0.14850648581010087,0.07109437185188841,-2.0888641666246923,-3.2393754503524565e-14 +-4.0,-0.10858858872468641,0.06522454108866148,-1.6648425103839215,-3.0271060429342046e-14 +-3.0,-0.06288342322853809,0.06000714503007155,-1.0479322620168838,-2.895668145826433e-14 +-2.0,-0.007429949914950523,0.055498453779690086,-0.13387670122207165,-3.2169539191587655e-14 +-1.0,0.05656004203302359,0.05159811771021331,1.0961648320327801,-3.44716398526909e-14 +0.0,0.12392449645064037,0.04839062569141725,2.5609194896733913,-3.597944298611074e-14 +1.0,0.19309362003485317,0.04593968204080192,4.203198878550238,-3.699581064093612e-14 +2.0,0.2625331911314792,0.044328371503610776,5.922464151657241,-3.6349856219703554e-14 +3.0,0.3323792213186091,0.04356996032047687,7.628632637574346,-3.6413469417385087e-14 +4.0,0.40297413442239444,0.04359394940688724,9.243808829092464,-3.773253515649088e-14 +5.0,0.4734826904404322,0.04438413803893367,10.667835658430365,-3.826806223929053e-14 +6.0,0.5430144326845379,0.04590240400649957,11.829760214903983,-4.0253505670851383e-14 +7.0,0.610689137470121,0.04806877475261435,12.704487281255428,-4.406262078692334e-14 +8.0,0.6758859112182876,0.05085291168580261,13.290997286336015,-4.723118897422392e-14 +9.0,0.7383699770457292,0.054242295408895566,13.612439729544315,-5.20455622927876e-14 +10.0,0.7982179068869607,0.05807229829781809,13.74524395079696,-5.5385868816441935e-14 +11.0,0.8557802537306283,0.062209616690946774,13.756398114170796,-5.702371714996311e-14 +12.0,0.8988323082495834,0.0690977304744752,13.008130687904623,-6.141415623852904e-14 +13.0,0.9147135983203839,0.08124056010481986,11.259321663220728,6.491282774779828e-13 +14.0,0.9112748609115651,0.0966853408597458,9.425160554933385,4.54748749597064e-13 +15.0,0.9085348699441353,0.11140779158846578,8.155038862095148,3.3836985824286487e-13 +16.0,0.9062580847970818,0.1257712798490804,7.2056043787146695,2.6754981159878576e-13 +17.0,0.8882638215990443,0.13985252773614038,6.3514320118327126,4.0927876403191203e-13 +18.0,0.8801641114980264,0.15426592918480644,5.7054990440800015,2.5988028226070375e-13 +19.0,0.8799535802082414,0.16798064710830107,5.238422373982847,1.821903726884496e-13 +20.0,0.8812698509369349,0.18370556270697425,4.797186530179459,1.3007693874618696e-13 +21.0,0.871379428960392,0.198621428734149,4.387137050185641,5.975307998613411e-15 +22.0,0.8680573492907033,0.21572711063981947,4.023867685040394,-1.822880946847326e-15 +23.0,0.8639910136639356,0.23075669712075686,3.7441644140529626,-5.408316146275571e-16 +24.0,0.8613474653095494,0.24594284553183446,3.5022261511488364,-4.729369019706576e-15 +25.0,0.8583553232582976,0.2571571564052344,3.3378628666498424,-7.613518753563846e-15 diff --git a/data/TUDELFT_V3_KITE/literature_results/V3_CL_CD_RANS_Lebesque_2024_Rey_300e4.csv b/data/TUDELFT_V3_KITE/literature_results/V3_CL_CD_RANS_Lebesque_2024_Rey_300e4.csv deleted file mode 100644 index 5bee35d1..00000000 --- a/data/TUDELFT_V3_KITE/literature_results/V3_CL_CD_RANS_Lebesque_2024_Rey_300e4.csv +++ /dev/null @@ -1,19 +0,0 @@ -CL,CD,aoa --0.114285714,0.0744,-5 --0.050793651,0.068,-4 -0.082539683,0.0552,-2 -0.247619048,0.0512,0 -0.4,0.052,2 -0.46984127,0.0528,3 -0.542857143,0.0576,4 -0.685714286,0.0656,6 -0.80952381,0.0776,8 -0.873015873,0.0832,9 -0.93015873,0.0928,10 -1.047619048,0.1104,12 -1.155555556,0.1296,14 -1.250793651,0.1504,16 -1.13015873,0.2024,18 -1.146031746,0.2248,20 -1.146031746,0.2252,22 -1.158730159,0.2816,24 diff --git a/data/TUDELFT_V3_KITE/literature_results/WindTunnel_Re_5e5_Poland2025_alpha_sweep_beta_0.csv b/data/TUDELFT_V3_KITE/literature_results/WindTunnel_Re_5e5_Poland2025_alpha_sweep_beta_0.csv new file mode 100644 index 00000000..b2a2be53 --- /dev/null +++ b/data/TUDELFT_V3_KITE/literature_results/WindTunnel_Re_5e5_Poland2025_alpha_sweep_beta_0.csv @@ -0,0 +1,18 @@ +CL,CL_ci,CD,CD_ci,alpha +-0.28023315356081796,0.011070533538875897,0.09785297775939765,0.012935829196785585,-11.568121157001665 +-0.2144913736143728,0.012287227041809052,0.06853577957407217,0.015525138484707877,-6.099059501611582 +-0.0007680391233001299,0.01068508564308875,0.04885867739007862,0.0076696455159627275,-1.9996385577164184 +0.07398995139159774,0.00953159417113588,0.05739081465627228,0.008889911090057321,-1.3348199670846914 +0.46519267467797903,0.009475707060472788,0.05616787766119728,0.009084810793467887,3.0810784665258444 +0.610180915884597,0.0045250228316688484,0.07431024337243476,0.004621689815286087,5.412846420261046 +0.7430356350927991,0.009465755795905533,0.08664306372317211,0.009633413459228232,7.350324457982788 +0.887298865863501,0.010638047578235603,0.10233695227784106,0.00900521264610847,9.382433604529174 +0.9255655151637727,0.014238431399063743,0.17599439630813363,0.01507120428946693,11.464425166301869 +0.9327251987983486,0.015877506028324398,0.18888674805756867,0.01693686866633114,12.461055790544702 +0.9512282813613351,0.014573344990978988,0.2127454401843595,0.018047053186439406,13.352348165878231 +0.9770715203611249,0.018103047941433924,0.22788683966364287,0.0204637541133525,14.540186234231973 +1.008562675819161,0.016658847313704747,0.24447585438450992,0.018378234971297258,16.225366370508798 +1.0681034642531901,0.0154900038338791,0.319919197381967,0.02298889264565519,18.29734623730859 +1.0099938012961718,0.015447658557709807,0.3573016324548397,0.015144711790384626,20.224692877134817 +0.9979635604848679,0.01181112128634061,0.4199851182071093,0.011605298627928523,23.03035435658158 +0.9749275179241531,0.01301729603627638,0.43498425522432616,0.012174929509637398,24.54119521035482 diff --git a/examples/V3_kite.jl b/examples/V3_kite.jl index 670d41bf..831283a5 100644 --- a/examples/V3_kite.jl +++ b/examples/V3_kite.jl @@ -10,63 +10,51 @@ yaw_rate = 0.0 # [rad/s] (not used in static analysis) air_density = 1.225 # [kg/m^3] Air density at sea level project_dir = dirname(dirname(pathof(VortexStepMethod))) # Go up one level from src to project root yaml_geometry_path = joinpath(project_dir, "data", "TUDELFT_V3_KITE", "geometry.yaml") +literature_paths = [ + # joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv"), + # joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv"), + joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","Python_VSM_Rey_5e5_Poland2025_alpha_sweep_beta_0.csv"), + # joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","WindTunnel_Re_5e5_Poland2025_alpha_sweep_beta_0.csv") + ] +labels= [ + "VSM Julia", + # "CFD RANS Re=5e5", + # "CFD RANS Re=10e5", + "Python VSM Re=5e5", + # "Wind Tunnel Re=5e5" + ] -println("=== Static Aerodynamic Analysis (VSM) ===") -println("Wind speed: $wind_speed m/s") -println("Angle of attack: $angle_of_attack_deg deg") -println("Sideslip: $sideslip_deg deg") +# println("=== Static Aerodynamic Analysis (VSM) ===") +# println("Wind speed: $wind_speed m/s") +# println("Angle of attack: $angle_of_attack_deg deg") +# println("Sideslip: $sideslip_deg deg") -# Create wing geometry from YAML (following RamAirWing pattern) -wing = YamlWing(yaml_geometry_path; n_panels=20, spanwise_distribution=LINEAR) +# Create wing, body_aero, and solver objects +wing = YamlWing(yaml_geometry_path; n_panels=40, spanwise_distribution=LINEAR) body_aero = BodyAerodynamics([wing]) - -# --- Set apparent wind vector in body axes --- -α = deg2rad(angle_of_attack_deg) -β = deg2rad(sideslip_deg) -va = wind_speed * [ - cos(α)*cos(β), # X_b (forward) - sin(β), # Y_b (right) - sin(α)*cos(β) # Z_b (down) -] -set_va!(body_aero, va) - -# --- Create and run VSM solver --- solver = Solver(body_aero; aerodynamic_model_type=VSM, is_with_artificial_damping=false, rtol=1e-5, solver_type=NONLIN ) -results = VortexStepMethod.solve(solver, body_aero; log=true) # Using plotting modules, to create more comprehensive plots PLOT = true USE_TEX = false -# Plotting geometry -PLOT && plot_geometry( - body_aero, - ""; - data_type=".svg", - save_path="", - is_save=false, - is_show=true, - view_elevation=15, - view_azimuth=-120, - use_tex=USE_TEX -) - # Plotting polars PLOT && plot_polars( [solver], [body_aero], - ["V3 Kite"], - angle_range=range(0, 25, length=20), + labels, + literature_path_list=literature_paths, + angle_range=range(5, 10, length=2), angle_type="angle_of_attack", - angle_of_attack=5, - side_slip=0, - v_a=10, + angle_of_attack=angle_of_attack_deg, + side_slip=sideslip_deg, + v_a=wind_speed, title="$(wing.n_panels)_distribution_$(wing.spanwise_distribution)", data_type=".pdf", is_save=false, @@ -74,19 +62,45 @@ PLOT && plot_polars( use_tex=USE_TEX ) -# Plotting spanwise distributions -body_y_coordinates = [panel.aero_center[2] for panel in body_aero.panels] -PLOT && plot_distribution( - [body_y_coordinates], - [results], - ["VSM"]; - title="CAD_spanwise_distributions_alpha_$(round(angle_of_attack_deg, digits=1))_delta_$(round(sideslip_deg, digits=1))_yaw_$(round(yaw_rate, digits=1))_v_a_$(round(wind_speed, digits=1))", - data_type=".pdf", - is_save=false, - is_show=true, - use_tex=USE_TEX -) +# # Plotting geometry +# --- Set apparent wind vector in body axes --- +# α = deg2rad(angle_of_attack_deg) +# β = deg2rad(sideslip_deg) +# va = wind_speed * [ +# cos(α)*cos(β), # X_b (forward) +# sin(β), # Y_b (right) +# sin(α)*cos(β) # Z_b (down) +# ] +# set_va!(body_aero, va) + +# results = VortexStepMethod.solve(solver, body_aero; log=true) +# PLOT && plot_geometry( +# body_aero, +# ""; +# data_type=".svg", +# save_path="", +# is_save=false, +# is_show=true, +# view_elevation=15, +# view_azimuth=-120, +# use_tex=USE_TEX +# ) + + +# # Plotting spanwise distributions +# body_y_coordinates = [panel.aero_center[2] for panel in body_aero.panels] + +# PLOT && plot_distribution( +# [body_y_coordinates], +# [results], +# ["VSM"]; +# title="CAD_spanwise_distributions_alpha_$(round(angle_of_attack_deg, digits=1))_delta_$(round(sideslip_deg, digits=1))_yaw_$(round(yaw_rate, digits=1))_v_a_$(round(wind_speed, digits=1))", +# data_type=".pdf", +# is_save=false, +# is_show=true, +# use_tex=USE_TEX +# ) nothing \ No newline at end of file diff --git a/src/plotting.jl b/src/plotting.jl index 504e8ecd..238618cf 100644 --- a/src/plotting.jl +++ b/src/plotting.jl @@ -645,15 +645,25 @@ function VortexStepMethod.plot_polars( # Update label with Reynolds number label_list[i] = "$(label_list[i]) Re = $(round(Int64, rey*1e-5))e5" end - # Load literature data if provided if !isempty(literature_path_list) for path in literature_path_list - # Read all data first data = readdlm(path, ',') - # Skip the header row by taking data from row 2 onwards - data = data[2:end, :] - push!(polar_data_list, [data[:, 3], data[:, 1], data[:, 2], zeros(length(data[:, 1]))]) + header = lowercase.(string.(data[1, :])) + # Find column indices for alpha, CL, CD, CS (case-insensitive, allow common variants) + alpha_idx = findfirst(x -> occursin("alpha", x), header) + cl_idx = findfirst(x -> occursin("cl", x), header) + cd_idx = findfirst(x -> occursin("cd", x), header) + cs_idx = findfirst(x -> occursin("cs", x), header) + # Fallback: if CS not found, fill with zeros + cs_col = cs_idx === nothing ? zeros(size(data, 1)-1) : data[2:end, cs_idx] + # Push as [alpha, CL, CD, CS] + push!(polar_data_list, [ + data[2:end, alpha_idx], + data[2:end, cl_idx], + data[2:end, cd_idx], + cs_col + ]) end end diff --git a/src/yaml_geometry.jl b/src/yaml_geometry.jl index eefff405..249afa49 100644 --- a/src/yaml_geometry.jl +++ b/src/yaml_geometry.jl @@ -211,7 +211,7 @@ function YamlWing( spanwise_distribution=LINEAR, spanwise_direction=[0.0, 1.0, 0.0], remove_nan=true, - prn=true + prn=false ) !(n_panels % n_groups == 0) && throw(ArgumentError("Number of panels should be divisible by number of groups")) !isapprox(spanwise_direction, [0.0, 1.0, 0.0]) && throw(ArgumentError("Spanwise direction has to be [0.0, 1.0, 0.0], not $spanwise_direction")) From e4ffc415b7b6f0c710ccde0995cf1d1439853be5 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Tue, 5 Aug 2025 08:58:48 +0200 Subject: [PATCH 08/26] #185 non-italic subscripts in plotting --- src/plotting.jl | 34 +++++++++++++++++----------------- 1 file changed, 17 insertions(+), 17 deletions(-) diff --git a/src/plotting.jl b/src/plotting.jl index 238618cf..3c602edb 100644 --- a/src/plotting.jl +++ b/src/plotting.jl @@ -349,9 +349,9 @@ function VortexStepMethod.plot_distribution(y_coordinates_list, results_list, la for (y_coordinates_i, result_i, label_i) in zip(y_coordinates_list, results_list, label_list) value = "$(round(result_i["cl"], digits=2))" if label_i == "LLT" - label = label_i * L" $~C_L$: " * value + label = label_i * L" $~C_\mathrm{L}$: " * value else - label = label_i * L" $C_L$: " * value + label = label_i * L" $C_\mathrm{L}$: " * value end axs[1, 1].plot( y_coordinates_i, @@ -359,18 +359,18 @@ function VortexStepMethod.plot_distribution(y_coordinates_list, results_list, la label=label ) end - axs[1, 1].set_title(L"$C_L$ Distribution", size=16) + axs[1, 1].set_title(L"$C_\mathrm{L}$ Distribution", size=16) axs[1, 1].set_xlabel(L"Spanwise Position $y/b$") - axs[1, 1].set_ylabel(L"Lift Coefficient $C_L$") + axs[1, 1].set_ylabel(L"Lift Coefficient $C_\mathrm{L}$") axs[1, 1].legend() # CD plot for (y_coordinates_i, result_i, label_i) in zip(y_coordinates_list, results_list, label_list) value = "$(round(result_i["cl"], digits=2))" if label_i == "LLT" - label = label_i * L" $~C_D$: " * value + label = label_i * L" $~C_\mathrm{D}$: " * value else - label = label_i * L" $C_D$: " * value + label = label_i * L" $C_\mathrm{D}$: " * value end axs[1, 2].plot( y_coordinates_i, @@ -378,9 +378,9 @@ function VortexStepMethod.plot_distribution(y_coordinates_list, results_list, la label=label ) end - axs[1, 2].set_title(L"$C_D$ Distribution", size=16) + axs[1, 2].set_title(L"$C_\mathrm{D}$ Distribution", size=16) axs[1, 2].set_xlabel(L"Spanwise Position $y/b$") - axs[1, 2].set_ylabel(L"Drag Coefficient $C_D$") + axs[1, 2].set_ylabel(L"Drag Coefficient $C_\mathrm{D}$") axs[1, 2].legend() # Gamma Distribution @@ -705,10 +705,10 @@ function VortexStepMethod.plot_polars( if maximum(polar_data[2]) > 10 axs[1, 1].set_ylim([-0.5, 2]) end - title = raw"$C_L" * raw"$" * " vs $angle_type [°]" + title = raw"$C_\mathrm{L}" * raw"$" * " vs $angle_type [°]" axs[1, 1].set_title(title) axs[1, 1].set_xlabel("$angle_type [°]") - axs[1, 1].set_ylabel(L"$C_L$") + axs[1, 1].set_ylabel(L"$C_\mathrm{L}$") axs[1, 1].legend() end @@ -745,10 +745,10 @@ function VortexStepMethod.plot_polars( if maximum(polar_data[2]) > 10 axs[1, 2].set_ylim([-0.5, 2]) end - title = raw"$C_D" * raw"$" * " vs $angle_type [°]" + title = raw"$C_\mathrm{D}" * raw"$" * " vs $angle_type [°]" axs[1, 2].set_title(title) axs[1, 2].set_xlabel("$angle_type [°]") - axs[1, 2].set_ylabel(L"$C_D$") + axs[1, 2].set_ylabel(L"$C_\mathrm{D}$") axs[1, 2].legend() end @@ -786,10 +786,10 @@ function VortexStepMethod.plot_polars( if maximum(polar_data[2]) > 10 axs[2, 1].set_ylim([-0.5, 2]) end - title = raw"$C_S" * raw"$" * " vs $angle_type [°]" + title = raw"$C_\mathrm{S}" * raw"$" * " vs $angle_type [°]" axs[2, 1].set_title(title) axs[2, 1].set_xlabel("$angle_type [°]") - axs[2, 1].set_ylabel(L"$C_S$") + axs[2, 1].set_ylabel(L"$C_\mathrm{S}$") axs[2, 1].legend() end @@ -827,10 +827,10 @@ function VortexStepMethod.plot_polars( axs[2, 2].set_ylim([-0.5, 2]) axs[2, 2].set_xlim([-0.5, 2]) end - title = raw"$C_L" * raw"$" * " vs " * raw"$C_D" * raw"$" + title = raw"$C_\mathrm{L}" * raw"$" * " vs " * raw"$C_\mathrm{D}" * raw"$" axs[2, 2].set_title(title) - axs[2, 2].set_xlabel(L"$C_D$") - axs[2, 2].set_ylabel(L"$C_L$") + axs[2, 2].set_xlabel(L"$C_\mathrm{D}$") + axs[2, 2].set_ylabel(L"$C_\mathrm{L}$") axs[2, 2].legend() end From cffe014d986d9a9ed06517e8bce1d37a84d92d38 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Tue, 5 Aug 2025 10:09:22 +0200 Subject: [PATCH 09/26] #185 , #186 : cleaned-up yaml_geometry, added a comparison to CFD - WindTunnel Data and Python --- data/TUDELFT_V3_KITE/2D_polars_CFD/1.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/10.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/11.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/12.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/13.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/14.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/15.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/16.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/17.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/18.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/19.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/2.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/3.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/4.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/5.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/6.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/7.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/8.csv | 71 ----------- data/TUDELFT_V3_KITE/2D_polars_CFD/9.csv | 71 ----------- .../2D_polars_CFD_re5e5_pchip_fitted/1.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/10.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/11.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/12.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/13.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/14.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/15.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/16.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/17.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/18.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/19.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/2.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/3.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/4.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/5.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/6.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/7.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/8.csv | 71 +++++++++++ .../2D_polars_CFD_re5e5_pchip_fitted/9.csv | 71 +++++++++++ ...geometry_CAD_CFD_polars_pchip_fitted.yaml} | 113 +++++++++--------- ...y_5e5_n36_CFD_PCHIP_polars_alpha_sweep.csv | 63 ++++++++++ examples/V3_kite.jl | 110 +++++++++-------- src/yaml_geometry.jl | 107 ++++++----------- 42 files changed, 1560 insertions(+), 1531 deletions(-) delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/1.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/10.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/11.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/12.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/13.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/14.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/15.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/16.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/17.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/18.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/19.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/2.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/3.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/4.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/5.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/6.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/7.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/8.csv delete mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD/9.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/1.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/10.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/11.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/12.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/13.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/14.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/15.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/16.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/17.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/18.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/19.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/2.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/3.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/4.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/5.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/6.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/7.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/8.csv create mode 100644 data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/9.csv rename data/TUDELFT_V3_KITE/{geometry.yaml => geometry_CAD_CFD_polars_pchip_fitted.yaml} (50%) create mode 100644 data/TUDELFT_V3_KITE/literature_results/Python_VSM_Rey_5e5_n36_CFD_PCHIP_polars_alpha_sweep.csv diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD/1.csv b/data/TUDELFT_V3_KITE/2D_polars_CFD/1.csv deleted file mode 100644 index 1b9cd368..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/1.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.0249065318608897,-3.434761974054366e-21,-1.0732064541182402,0.0054067639622245 --9.5,0.0236873271741019,-3.285535810591269e-21,-1.0370727681402363,0.0058564293781756 --9.0,0.0225262393305432,-3.1355323293482928e-21,-0.9992907398617008,0.0062213900212979 --8.5,0.0214269325718191,-2.984782761608788e-21,-0.9599576821061372,0.0065104482864488 --8.0,0.0203930711395351,-2.833318338656105e-21,-0.9191709076970505,0.006732406568486 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7c56f03a..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/10.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.1301765524838856,1.5332052308649837e-21,-0.3263185917913435,0.0618002947702435 --9.5,0.1257890360417442,1.5315041094699052e-21,-0.3261426062537052,0.0666892655945722 --9.0,0.1212879340769155,1.5264915255975585e-21,-0.3256084156736321,0.0706040503505845 --8.5,0.116679079686172,1.518303649717276e-21,-0.3247066691003862,0.07365289193476 --8.0,0.1119683059662863,1.5070766522983917e-21,-0.3234280155832302,0.0759440332435782 --7.5,0.1071614460140309,1.4929467038102385e-21,-0.3217631041714262,0.0775857171735189 --7.0,0.1022643329261784,1.4760499747221493e-21,-0.3197025839142366,0.0786861866210615 --6.5,0.0972827997995013,1.4565226355034568e-21,-0.3172371038609237,0.0793536844826857 --6.0,0.0922226797307723,1.4345008566234952e-21,-0.31435731306075,0.0796964536548711 --5.5,0.0870898058167638,1.4101208085515973e-21,-0.3110538605629776,0.0798227370340973 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-22.5,0.3407911991926162,-2.6900748997074535e-21,1.023728034663366,-0.1722439247841423 -23.0,0.3506252677373594,-2.7131480478888718e-21,1.0261072582221118,-0.1735016467457813 -23.5,0.3603646238253482,-2.733038105464505e-21,1.0295036757149931,-0.1747573484906663 -24.0,0.3700078925965967,-2.7490414202107677e-21,1.0334517784197144,-0.1760110251474264 -24.5,0.3795536991911191,-2.760454339904076e-21,1.0374860576139795,-0.1772626718446905 diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD/11.csv b/data/TUDELFT_V3_KITE/2D_polars_CFD/11.csv deleted file mode 100644 index fa9933c0..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/11.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.0960543185292821,1.893877927263632e-21,-0.1761399982678887,0.0431407405021115 --9.5,0.0876796098717111,1.836113520681478e-21,-0.1266327311081181,0.0369558977635774 --9.0,0.0799145997431278,1.7856100883133313e-21,-0.0853937545713418,0.0320034591131645 --8.5,0.0728233188699501,1.742089576065367e-21,-0.051703031622221,0.0281464907633038 --8.0,0.0664697979785958,1.7052739298437612e-21,-0.0248405252254165,0.0252480589264262 --7.5,0.0609180677954828,1.6748850955546893e-21,-0.0040861983455891,0.0231712298149628 --7.0,0.0562321590470291,1.6506450191043272e-21,0.0112799860526,0.0217790696413444 --6.5,0.0524761024596524,1.6322756463988506e-21,0.0219780650044903,0.0209346446180021 --6.0,0.0497139287597708,1.6194989233444356e-21,0.0287280755454206,0.0205010209573669 --5.5,0.048009668673802,1.6120367958472577e-21,0.0322500547107302,0.0203412648718697 --5.0,0.047427352928164,1.6096112098134926e-21,0.0332640395357581,0.0203184425739416 --4.5,0.0479651893273892,1.6204871115389689e-21,0.0191461595903086,0.0233525981869367 --4.0,0.0493097803254522,1.6476768658526593e-21,-0.0161485402733149,0.0309379872194245 --3.5,0.0510577486229341,1.6830235464604568e-21,-0.0620316500960256,0.0407989929616587 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-19.0,0.2705093321234093,3.9719219986427613e-22,1.0186464258738996,-0.1624334715769309 -19.5,0.2816975820457539,3.9318130245467873e-22,1.0186178746472492,-0.1646308110238051 -20.0,0.2923995497711874,3.8857937188555255e-22,1.0186048968169534,-0.1664227197836923 -20.5,0.3024568515553722,3.8181732333981243e-22,1.018899070622947,-0.1677790997909075 -21.0,0.3120773057518812,3.721018532449205e-22,1.0196767193441865,-0.1689017555307578 -21.5,0.3215402368504375,3.611812445086458e-22,1.02078053393556,-0.1699502305940275 -22.0,0.3311249693407643,3.5080378003875746e-22,1.0220532053519564,-0.1710840685715006 -22.5,0.3408782925586565,3.412603794300539e-22,1.0237895459228592,-0.1723324469289635 -23.0,0.3506606939664546,3.3167660793512267e-22,1.0262725023095218,-0.1736172400593201 -23.5,0.3604720452436998,3.2205271694841624e-22,1.0293269669644896,-0.1749370369440311 -24.0,0.3703122180699332,3.1238895786438725e-22,1.0327778323403063,-0.1762904265645569 -24.5,0.380181084124696,3.026855820774882e-22,1.036449990889516,-0.1776759979023581 diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD/12.csv b/data/TUDELFT_V3_KITE/2D_polars_CFD/12.csv deleted file mode 100644 index 37289943..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/12.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.1108116522876312,-1.3318470367061016e-21,-0.2498681581466391,0.0544674891510176 --9.5,0.1100126156963255,-1.349847415847465e-21,-0.2782826360085718,0.0626251953963974 --9.0,0.108661324343371,-1.3642610035732061e-21,-0.3010351883924809,0.0691573808401148 --8.5,0.1068149803235472,-1.3754863322628385e-21,-0.3187549181292581,0.0742446589045768 --8.0,0.1045307857316339,-1.383921934295876e-21,-0.3320709280497948,0.0780676430121902 --7.5,0.1018659426624106,-1.3899663420518318e-21,-0.3416123209849826,0.080806946585362 --7.0,0.098877653210657,-1.39401808791022e-21,-0.3480081997657128,0.0826431830464991 --6.5,0.0956231194711527,-1.396475704250554e-21,-0.351887667222877,0.0837569658180086 --6.0,0.0921595435386774,-1.3977377234523468e-21,-0.3538798261873668,0.0843289083222972 --5.5,0.0885441275080108,-1.3982026778951125e-21,-0.3546137794900736,0.0845396239817719 --5.0,0.0848340734739325,-1.3982690999583648e-21,-0.3547186299618888,0.0845697262188398 --4.5,0.0800836729244058,-1.385002918189812e-21,-0.3390420721318088,0.0824202362403489 --4.0,0.0738241294714341,-1.3496116879514008e-21,-0.2975984061101417,0.0766693384999171 --3.5,0.0668280133958569,-1.2987063818440037e-21,-0.2387666430997469,0.0683633912901055 --3.0,0.0598678949785136,-1.2388979724684924e-21,-0.1709257943034837,0.0585487529034754 --2.5,0.0537163445002438,-1.176797432425739e-21,-0.1024548709242114,0.048271781632588 --2.0,0.0491459322418869,-1.1190157343166153e-21,-0.0417328841647893,0.0385788357700045 --1.5,0.0460198824176772,-1.0626094085345268e-21,0.0108016201426883,0.0287818427960436 --1.0,0.0434667946336675,-1.0015675739508945e-21,0.0629127836869984,0.0179206732091829 --0.5,0.0411573022584248,-9.37900085883617e-22,0.1185256265465884,0.0066335998292219 -0.0,0.0387620386605163,-8.736167996505914e-22,0.1815651687999054,-0.00444110452404 -0.5,0.0360277402419184,-8.026498932354609e-22,0.2593901937291751,-0.0161780859490238 -1.0,0.0331846315804466,-7.260537042627391e-22,0.3500935222692885,-0.0285694725924971 -1.5,0.0306285783084259,-6.565213275116307e-22,0.4437012309776902,-0.0396532147071796 -2.0,0.0287554460581816,-6.0674585776133935e-22,0.5302393964118252,-0.0474672625457916 -2.5,0.0273734877675563,-5.741403527997946e-22,0.6101476220352305,-0.0528786805729058 -3.0,0.0260524001510539,-5.468439547491757e-22,0.6898316789875413,-0.0579783635392763 -3.5,0.0248302145059911,-5.236388848900617e-22,0.7682668953403492,-0.0626400071268947 -4.0,0.0237449621296843,-5.033073645030322e-22,0.8444285991652458,-0.0667373070177529 -4.5,0.0228346743194502,-4.8463161486866655e-22,0.9172921185338228,-0.0701439588938422 -5.0,0.0221373823726053,-4.663938572675436e-22,0.9858327815176716,-0.0727336584371545 -5.5,0.0216911175864663,-4.473763129802429e-22,1.049025916188384,-0.0743801013296813 -6.0,0.0215339112583496,-4.263612032873436e-22,1.1058468506175525,-0.0749569832534144 -6.5,0.0216943861329512,-4.0153280868077904e-22,1.1603543969572097,-0.074507731309572 -7.0,0.022164722519717,-3.732726492723792e-22,1.2158127653632609,-0.0733233398212604 -7.5,0.0229282880630885,-3.436588057725685e-22,1.2700053809131018,-0.0716488553033025 -8.0,0.0239684504075072,-3.147693588917716e-22,1.320715668684131,-0.0697293242705215 -8.5,0.0252685771974145,-2.886823893404127e-22,1.365727053753745,-0.0678097932377406 -9.0,0.0268120360772519,-2.6747597782891667e-22,1.4028229611993408,-0.0661353087197827 -9.5,0.0285821946914609,-2.5322820506770768e-22,1.4297868160983158,-0.0649509172314711 -10.0,0.030562420684483,-2.4801715176721034e-22,1.444402043528067,-0.0645016652876288 -10.5,0.033947291609916,-2.667671390795412e-22,1.4516441332414538,-0.0659314512090525 -11.0,0.0396370854660977,-3.1292778860473e-22,1.4575640586070189,-0.0696306731606777 -11.5,0.0471737205645791,-3.713651317250717e-22,1.4615584701256823,-0.0747141274235352 -12.0,0.0560991152169112,-4.2694519982286085e-22,1.4630240182983656,-0.0802966102786558 -12.5,0.0693414270904374,-4.761379328064538e-22,1.4262343401997868,-0.087566346162779 -13.0,0.0880475223680259,-5.27162377779413e-22,1.3403602522005649,-0.0972330503834448 -13.5,0.1090873821345145,-5.825082269168435e-22,1.242144173745472,-0.1076937555278846 -14.0,0.1293309874747411,-6.446651723938501e-22,1.16832852427928,-0.1173454941833299 -14.5,0.1493001928768931,-7.348212854597182e-22,1.1179442381309437,-0.1266759763438967 -15.0,0.1702213055110796,-8.470537482673554e-22,1.0709646503429533,-0.1362555628862974 -15.5,0.19002098548502,-9.431859193472993e-22,1.0355457814303837,-0.1446052627216575 -16.0,0.2066258929064338,-9.85041157230088e-22,1.0198436519083096,-0.1502460847611022 -16.5,0.2197502124794184,-9.867908450364604e-22,1.0170662874265095,-0.1535543825939099 -17.0,0.2310977030215999,-9.880515668444394e-22,1.0150186977848918,-0.1560965423745395 -17.5,0.2415793858109914,-9.888144826204874e-22,1.0137523797237242,-0.1581786218618874 -18.0,0.2521062821256056,-9.890707523310673e-22,1.0133188299832752,-0.16010667881485 -18.5,0.262809036793946,-9.82586357529844e-22,1.0136701316119383,-0.1619548396691582 -19.0,0.2732541891098212,-9.664075964789728e-22,1.0145356433442807,-0.163621088819349 -19.5,0.2835066020492019,-9.454461042076518e-22,1.0156327754498318,-0.1651472709625278 -20.0,0.2936311385880585,-9.24613515745079e-22,1.0166789381981205,-0.1665752307958001 -20.5,0.303586707643546,-9.029996945776452e-22,1.0175624838015755,-0.1678803838947653 -21.0,0.3133637585369111,-8.782618862617954e-22,1.018452836011624,-0.1690705478946611 -21.5,0.3230744648502615,-8.531627989318095e-22,1.0194890124062952,-0.1702361705820497 -22.0,0.3328310001657054,-8.304651407219669e-22,1.020810030563618,-0.1714676997434936 -22.5,0.3426520800934332,-8.104018796916546e-22,1.0227205256777256,-0.1727832632242773 -23.0,0.3524816305780461,-7.914468996760718e-22,1.025330103430928,-0.1741395800856049 -23.5,0.3623196407032684,-7.737242824732138e-22,1.0284852371335185,-0.1755349849379175 -24.0,0.372166099552824,-7.573581098810767e-22,1.0320324000957908,-0.1769678123916567 -24.5,0.382020996210437,-7.424724636976561e-22,1.0358180656280378,-0.1784363970572636 diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD/13.csv b/data/TUDELFT_V3_KITE/2D_polars_CFD/13.csv deleted file mode 100644 index 5fbcca13..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/13.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.122546573076266,1.242138678946769e-21,-0.3088564506446254,0.0605061143794596 --9.5,0.11793215005532,1.3525325021944349e-21,-0.3195972925667664,0.0685369351208477 --9.0,0.1133972670998442,1.4409290322488389e-21,-0.328197892925086,0.0749675185189335 --8.5,0.1089402624630475,1.5097724127981217e-21,-0.3348960563377865,0.0799756687229726 --8.0,0.1045594743981387,1.5615067875304229e-21,-0.3399295874230703,0.0837391898822209 --7.5,0.1002532411583269,1.5985763001338829e-21,-0.3435362907991398,0.0864358861459343 --7.0,0.0960199009968208,1.6234250942966414e-21,-0.3459539710841974,0.0882435616633685 --6.5,0.0918577921668296,1.6384973137068396e-21,-0.3474204328964455,0.0893400205837794 --6.0,0.0877652529215621,1.646237102052617e-21,-0.3481734808540863,0.0899030670564229 --5.5,0.0837406215142272,1.6490886030221137e-21,-0.3484509195753224,0.0901105052305547 --5.0,0.0797822361980339,1.6494959603034701e-21,-0.3484905536783562,0.0901401392554307 --4.5,0.0759966790705553,1.6087886429285233e-21,-0.3363103253503615,0.0870092662603577 --4.0,0.0724133906467291,1.498868465365949e-21,-0.3033345494286829,0.0786849739544894 --3.5,0.0689149968058109,1.3380380894591469e-21,-0.2549105895067778,0.0667697523568515 --3.0,0.0653841234270563,1.144600177051517e-21,-0.1963858091781041,0.0528660914864699 --2.5,0.0617033963897211,9.368573899864588e-22,-0.1331075720361196,0.0385764813623703 --2.0,0.0577554415730607,7.331123901073714e-22,-0.0704232416742819,0.0255034120035786 --1.5,0.0531604798030625,5.0203032358094e-22,0.000346895729077,0.0123827430972856 --1.0,0.0480844972012635,2.2606271847664062e-22,0.0853369159166389,-0.0019441069590179 --0.5,0.0432287675902434,-5.580819050793926e-23,0.1753809981764662,-0.0157163100808566 -0.0,0.0392945647925822,-3.0460016867521196e-22,0.2613133217966217,-0.027173038183755 -0.5,0.0361804650476932,-5.205207443065566e-22,0.3421577447146814,-0.0366809325513925 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-17.5,0.2286381355069146,-2.6230144403769888e-21,1.046414087800535,-0.1528956312235985 -18.0,0.2384113843227168,-2.6370522560810336e-21,1.0534104027344486,-0.1548922744724667 -18.5,0.2486050830858552,-2.6544998888087336e-21,1.057245373355475,-0.1570251757934053 -19.0,0.2588549945995975,-2.673326273502652e-21,1.0604431328030588,-0.1591503236707561 -19.5,0.269120172800051,-2.692695164465989e-21,1.0630028162169998,-0.1612286806868206 -20.0,0.279359671623323,-2.711770316001944e-21,1.0649235587370989,-0.1632212094239005 -20.5,0.2896096180420362,-2.730819863737853e-21,1.0663709390996077,-0.1651497032067279 -21.0,0.2998762055970267,-2.7501261259156168e-21,1.0675518856890431,-0.1670305940109098 -21.5,0.3100735880767218,-2.7688741307602845e-21,1.0685275581176044,-0.1688168023950605 -22.0,0.3201159192695488,-2.7862489064969054e-21,1.0693591159974902,-0.1704612489177939 -22.5,0.3299931015740035,-2.802274882380748e-21,1.0701085066211145,-0.1719772817242464 -23.0,0.339750737250688,-2.817461526589377e-21,1.0707780845611057,-0.1734019280833753 -23.5,0.3493865298811888,-2.831721425731287e-21,1.071339620349982,-0.1747236272395255 -24.0,0.3588981830470925,-2.8449671664149728e-21,1.0717648845202643,-0.1759308184370421 -24.5,0.3682834003299856,-2.8571113352489288e-21,1.0720256476044712,-0.17701194092027 diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD/14.csv b/data/TUDELFT_V3_KITE/2D_polars_CFD/14.csv deleted file mode 100644 index c01ffb80..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/14.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.1247963862531487,-8.263188570309638e-22,-0.4377847767021424,0.1291313592352408 --9.5,0.1225027687600532,-8.2510064848077645e-22,-0.4367631614049428,0.1287374262101457 --9.0,0.1197867284636386,-8.214602594815178e-22,-0.433752535163911,0.1275964699383671 --8.5,0.116683774139274,-8.154190450101442e-22,-0.4288342274548969,0.1257697546251651 --8.0,0.1132294145623286,-8.069983600436115e-22,-0.4220895677537509,0.1233185444757994 --7.5,0.1094591585081718,-7.962195595588752e-22,-0.413599885536323,0.1203041036955302 --7.0,0.1054085147521727,-7.831039985328916e-22,-0.4034465102784633,0.1167876964896174 --6.5,0.1011129920697006,-7.676730319426165e-22,-0.391710771456022,0.1128305870633209 --6.0,0.0966080992361246,-7.49948014765006e-22,-0.3784739985448493,0.1084940396219008 --5.5,0.091929345026814,-7.299503019770156e-22,-0.3638175210207952,0.1038393183706169 --5.0,0.087112238217138,-7.077012485556013e-22,-0.34782266835971,0.0989276875147293 --4.5,0.0812978211166936,-6.488937178685686e-22,-0.3179983719550545,0.0918592212243729 --4.0,0.0741407037300396,-5.332907702632524e-22,-0.2666828564668877,0.0814800188661822 --3.5,0.0664467463749878,-3.8201905618590233e-22,-0.201201391270957,0.0689703824401658 --3.0,0.0590218093693501,-2.1620522608276884e-22,-0.1288792457430095,0.0555106139463327 --2.5,0.0526717530309383,-5.697593040010157e-23,-0.0570416892587924,0.0422810153846915 --2.0,0.0482024376775642,7.454218041584896e-23,0.0069860088059468,0.0304618887552512 --1.5,0.0452825311470559,1.7490318094995511e-22,0.0617885315846021,0.0201400959698438 --1.0,0.0429190595046173,2.641083628223872e-22,0.114267179253653,0.0102637758761647 --0.5,0.0409254204091241,3.562019011398432e-22,0.1695716080019811,0.0003051458780172 -0.0,0.0391150115194519,4.652279710090204e-22,0.2328514740184679,-0.0102635766207953 -0.5,0.03746604740574,6.084850061181858e-22,0.3127080581892902,-0.0233230377654791 -1.0,0.0360105821295864,7.794350854553734e-22,0.4063624679615703,-0.038065759761187 -1.5,0.0346427725870538,9.563678520769309e-22,0.5018940993656077,-0.0509873392940356 -2.0,0.0332567756742054,1.1175729490392057e-21,0.5873823484317017,-0.0585833730501417 -2.5,0.031683897345946,1.263226790371277e-21,0.6627729640342712,-0.0621617401132827 -3.0,0.0299103346892531,1.4070349588153766e-21,0.7357900118512681,-0.0653489298848937 -3.5,0.0280625812982984,1.5475808504975841e-21,0.8061803631182909,-0.0681184545275775 -4.0,0.0262671307672536,1.6834478615439786e-21,0.8736908890709383,-0.0704438262039368 -4.5,0.0246504766902903,1.8132193880806402e-21,0.9380684609448092,-0.0722985570765744 -5.0,0.0233391126615801,1.935478826233648e-21,0.9990599499755022,-0.0736561593080931 -5.5,0.0224595322752949,2.0488095721290807e-21,1.056412227398616,-0.0744901450610956 -6.0,0.0221382291256061,2.1517950218930176e-21,1.1098721644497491,-0.0747740264981848 -6.5,0.0223314640591147,2.2531535594222814e-21,1.162780224196327,-0.0746178781265751 -7.0,0.0228962952147989,2.358874616778922e-21,1.2171567318066538,-0.074206214237786 -7.5,0.0238104121253965,2.46344816233686e-21,1.2707683516676482,-0.0736242066708773 -8.0,0.025051504323645,2.561364164470016e-21,1.321381748166228,-0.0729570272649089 -8.5,0.0265972613422823,2.6471125915523125e-21,1.3667635856893123,-0.0722898478589404 -9.0,0.0284253727140459,2.715183411957669e-21,1.4046805286238184,-0.0717078402920317 -9.5,0.0305135279716735,2.760066594060008e-21,1.4328992413566646,-0.0712961764032426 -10.0,0.0328394166479028,2.776252106233249e-21,1.4491863882747698,-0.071140028031633 -10.5,0.0366810831271125,2.7516724629994485e-21,1.458269654582415,-0.0730563533135527 -11.0,0.043019831321635,2.6896488391285578e-21,1.4658028460109478,-0.0779222172837384 -11.5,0.0513882400561384,2.607754193366343e-21,1.4709418077378875,-0.0844129521288296 -12.0,0.0613188881552907,2.52356148445857e-21,1.4728423849407524,-0.0912038900354658 -12.5,0.0765664918929331,2.418802429364716e-21,1.4283217006273068,-0.0992505875285004 -13.0,0.0982239311313342,2.2879711349020934e-21,1.326134507421061,-0.1092386212719616 -13.5,0.1218310300778026,2.167784144603219e-21,1.2133430949231514,-0.1194383536612504 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-19.5,0.2844384801135907,1.922147694658312e-21,1.0263035407070953,-0.1676808564433322 -20.0,0.2943426002772124,1.9136352088652777e-21,1.0278215853181298,-0.1690211737595524 -20.5,0.3042872652961443,1.9014448525335597e-21,1.0289959236816688,-0.1703375066314811 -21.0,0.3141918464710955,1.886225069761821e-21,1.030101121442468,-0.1715866752227217 -21.5,0.3240591226655399,1.869761246300029e-21,1.031331124325448,-0.1728205478792933 -22.0,0.3338918727429516,1.853838767898152e-21,1.0328798780555286,-0.1740909929472152 -22.5,0.3436909069373617,1.838754662863472e-21,1.0350144626907467,-0.1754074872356527 -23.0,0.3534550566925633,1.8236158972400344e-21,1.0377872954044471,-0.1767446260801238 -23.5,0.3631841326866735,1.8084227633829577e-21,1.0410703275945117,-0.1781019556161763 -24.0,0.3728779455978093,1.7931755536473564e-21,1.0447355106588214,-0.1794790219793582 -24.5,0.3825363061040877,1.777874560388348e-21,1.0486547959952586,-0.1808753713052172 diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD/15.csv b/data/TUDELFT_V3_KITE/2D_polars_CFD/15.csv deleted file mode 100644 index accf0a4b..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/15.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.1130805978335641,-6.487203008152812e-22,-0.2539629024495576,0.0578101742159575 --9.5,0.1106801847109277,-7.492038958907563e-22,-0.271843172856166,0.0659134178650412 --9.0,0.1080076741625252,-8.296649295858784e-22,-0.2861605849529705,0.0724019930379238 --8.5,0.1050834747826947,-8.923281309429089e-22,-0.2973110118855049,0.077455307343072 --8.0,0.1019279951657744,-9.394182290041094e-22,-0.3056903267993029,0.0812527683889526 --7.5,0.0985616439061023,-9.731599528117412e-22,-0.3116944028398983,0.0839737837840324 --7.0,0.0950048295980167,-9.957780314080656e-22,-0.3157191131528249,0.0857977611367782 --6.5,0.0912779608358555,-1.0094971938353445e-21,-0.3181603308836165,0.0869041080556567 --6.0,0.087401446213957,-1.0165421691358392e-21,-0.3194139291778068,0.0874722321491349 --5.5,0.0833956943266593,-1.019137686351811e-21,-0.3198757811809295,0.0876815410256795 --5.0,0.0792811137683006,-1.0195084745255212e-21,-0.3199417600385185,0.0877114422937574 --4.5,0.074323557469085,-9.88311526382966e-22,-0.3037392851146056,0.0852922936464342 --4.0,0.0682764206649561,-9.0497769022907e-22,-0.2607608931452114,0.0787628889665007 --3.5,0.0618914254088603,-7.848924784744874e-22,-0.1994501333338529,0.0692152901470111 --3.0,0.0559202937537445,-6.43441403529873e-22,-0.1282505548840471,0.0577415590810194 --2.5,0.0511147477525552,-4.960099778058811e-22,-0.0556057069993109,0.0454337576615797 --2.0,0.0482265094582392,-3.5798371371316643e-22,0.0100408611168386,0.0333839477817462 --1.5,0.046931754245449,-2.0652291781113048e-22,0.0705793198362689,0.0187391023050391 --1.0,0.046101100235593,-3.245726186008608e-23,0.1333868718872297,0.0008069903166728 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-21.5,0.3301331219664806,1.1597659404861369e-21,1.0206783104281902,-0.1743665224553782 -22.0,0.3396067314372485,1.1543564683243581e-21,1.022969134242415,-0.1753799121661584 -22.5,0.3490212004898601,1.154378278476221e-21,1.025615081731637,-0.1764507317468222 -23.0,0.35836378772683,1.154530949539262e-21,1.0285095069878365,-0.1775347922678333 -23.5,0.3676336404558954,1.1549453424246585e-21,1.031627503895833,-0.178631860995498 -24.0,0.3768299059847928,1.1557523180435886e-21,1.0349441663404446,-0.1797417051961231 -24.5,0.385951731621259,1.1570827373072305e-21,1.0384345882064925,-0.1808640921360148 diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD/16.csv b/data/TUDELFT_V3_KITE/2D_polars_CFD/16.csv deleted file mode 100644 index e4bfbb84..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/16.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.0690531428236168,1.7060470918952625e-21,0.5968718755880111,0.1383778081326868 --9.5,0.0731139814098071,1.4850715925359193e-21,0.4054991655282779,0.1345881704479909 --9.0,0.0763225429293788,1.283057605587215e-21,0.2429018609374837,0.1302747918321246 --8.5,0.0787262908443322,1.099355920874026e-21,0.1072202868246507,0.1254607779277783 --8.0,0.0803726886166673,9.333173282212279e-22,-0.003405231801199,0.1201692343776428 --7.5,0.0813091997083842,7.842926174536984e-22,-0.0908343699310434,0.1144232668244087 --7.0,0.0815832875814831,6.516325783963129e-22,-0.1569268025558604,0.1082459809107667 --6.5,0.0812424156979641,5.346880008739479e-22,-0.2035422046666279,0.1016604822794075 --6.0,0.0803340475198273,4.328096747114799e-22,-0.2325402512543238,0.0946898765730217 --5.5,0.0789056465090729,3.453483897337849e-22,-0.245780617309926,0.0873572694343 --5.0,0.077004676127701,2.7165493576573942e-22,-0.2451229778244124,0.0796857665059331 --4.5,0.0746785998377116,2.1108010263221976e-22,-0.2324270077887609,0.0716984734306115 --4.0,0.071974881101105,1.6297468015810226e-22,-0.2095523821939495,0.0634184958510261 --3.5,0.0689409833798812,1.2668945816826316e-22,-0.1783587760309559,0.0548689394098674 --3.0,0.0656243701360405,1.0157522648757888e-22,-0.1407058642907583,0.0460729097498261 --2.5,0.0620725048315829,8.698277494092566e-23,-0.0984533219643345,0.0370535125135928 --2.0,0.0583328509285085,8.226289335317984e-23,-0.0534608240426624,0.0278338533438584 --1.5,0.0536625275289291,9.283522014626436e-23,0.0044901925590222,0.0177188109770728 --1.0,0.048108760314807,1.1963431880783822e-22,0.0798455012188159,0.0068425353430587 --0.5,0.0429041726179178,1.5528336676138185e-22,0.162086242385739,-0.0035279611254341 -0.0,0.0392813877700374,1.9240554143037576e-22,0.2406935565088119,-0.0121256659956565 -0.5,0.0369084996721764,2.3238751257628397e-22,0.3154312271056851,-0.01949888127879 -1.0,0.0346442661592727,2.80582249815507e-22,0.3925364188619867,-0.0269493013907456 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-23.5,0.3627018076991485,9.481704294022396e-22,1.0521736813086475,-0.1791246281270967 -24.0,0.3720501939476145,9.382464428393708e-22,1.055112863601373,-0.1802100095473852 -24.5,0.3812280875911373,9.28025884863756e-22,1.058151077583657,-0.1811604558012407 diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD/17.csv b/data/TUDELFT_V3_KITE/2D_polars_CFD/17.csv deleted file mode 100644 index 2a3a0380..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/17.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.1057662723266884,-5.817018081480684e-22,-0.2092124253447052,0.0469896304595866 --9.5,0.1052957010715932,-4.734389480172327e-22,-0.2466178348105712,0.0621002006194652 --9.0,0.1042474674393535,-3.849754995837386e-22,-0.2765697678515046,0.0741998084596632 --8.5,0.1026843064537022,-3.1433216819484437e-22,-0.29989638851472,0.083623005349034 --8.0,0.1006689531383717,-2.595296591978084e-22,-0.3174258608474321,0.090704342656431 --7.5,0.0982641425170949,-2.1858867793988958e-22,-0.3299863488968558,0.0957783717507076 --7.0,0.0955326096136044,-1.8952992976834585e-22,-0.3384060167102056,0.0991796440007172 --6.5,0.0925370894516329,-1.7037412003043604e-22,-0.3435130283346966,0.1012427107753131 --6.0,0.0893403170549131,-1.5914195407341858e-22,-0.3461355478175433,0.1023021234433489 --5.5,0.0860050274471777,-1.5385413724455196e-22,-0.3471017392059605,0.1026924333736779 --5.0,0.0825939556521595,-1.525313748910944e-22,-0.347239766547163,0.1027481919351535 --4.5,0.0780802277541945,-1.7715964980900917e-22,-0.3269921175983495,0.0985029128358534 --4.0,0.0719517644096791,-2.41812710193114e-22,-0.27405300988443,0.0874577852237359 --3.5,0.0650434925004361,-3.3264290948894963e-22,-0.200128202104186,0.0721488736274745 --3.0,0.0581903389082884,-4.358026011420568e-22,-0.1169234529563987,0.0551122425757432 --2.5,0.0522272305150588,-5.374441385979766e-22,-0.0361445211398498,0.0388839565972156 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72b8b355..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/18.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.1178787827507014,2.2656491307368418e-21,-0.2814872625103468,0.0602664033808302 --9.5,0.1142507070232501,2.1965336476654047e-21,-0.2839011290559559,0.0696954559408632 --9.0,0.1105121725280339,2.1307381956803045e-21,-0.2858340037437684,0.0772456566992661 --8.5,0.1066690702088321,2.068483790282197e-21,-0.2873393301135394,0.083125766967331 --8.0,0.1027272910094239,2.0099914469717408e-21,-0.2884705517050241,0.0875445480563502 --7.5,0.0986927258735886,1.9554821812495918e-21,-0.2892811120579777,0.0907107612776159 --7.0,0.0945712657451054,1.9051770086164077e-21,-0.2898244547121554,0.0928331679424204 --6.5,0.0903688015677535,1.8592969445728453e-21,-0.2901540232073125,0.0941205293620559 --6.0,0.0860912242853124,1.8180630046195626e-21,-0.2903232610832038,0.0947816068478146 --5.5,0.0817444248415611,1.7816962042572158e-21,-0.2903856118795849,0.0950251617109889 --5.0,0.0773342941802791,1.7504175589864634e-21,-0.2903945191362108,0.095059955262871 --4.5,0.0725303144755632,1.7253526692401192e-21,-0.2745948358205378,0.0916753329315969 --4.0,0.0672375819926454,1.7056461348793126e-21,-0.2329232913132488,0.0827992713844004 --3.5,0.0618154088120074,1.6885474705471688e-21,-0.1739711437739392,0.0703484787912198 --3.0,0.0566231070141306,1.6713061908868149e-21,-0.1063296513622039,0.0562396633219932 --2.5,0.0520199886794967,1.651171810541376e-21,-0.0385900722376382,0.0423895331466591 --2.0,0.0483653658885874,1.625393844153978e-21,0.0206563354401628,0.0307147964351559 --1.5,0.0456420538066005,1.5902813989344429e-21,0.0705129016762515,0.0211530252883604 --1.0,0.0433911184131789,1.5457961004140793e-21,0.1189365431002431,0.0120462979527718 --0.5,0.041309248010471,1.494666240718247e-21,0.1706163814893863,0.0029180818167614 -0.0,0.0390931309006255,1.4396201119723053e-21,0.2302415386209301,-0.0067081557312996 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-22.5,0.3496712891607121,1.3680397007987672e-22,1.0317442024037942,-0.1781520924765998 -23.0,0.3591964411842704,1.3127879406820628e-22,1.0352270281298783,-0.1794902139296338 -23.5,0.3686284683004163,1.2228434181311712e-22,1.0393064054841965,-0.1808766488774509 -24.0,0.3779659981468824,1.099958469399959e-22,1.0438420236147694,-0.1823088279547092 -24.5,0.3872076583614013,9.458854307422936e-23,1.0486935716696175,-0.1837841817960667 diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD/19.csv b/data/TUDELFT_V3_KITE/2D_polars_CFD/19.csv deleted file mode 100644 index 0ac18aa3..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/19.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.1759893858334057,2.9638190783935527e-21,-0.7493726713784946,0.2323775006207747 --9.5,0.1628973492460343,2.7877286866584318e-21,-0.6924217529040287,0.2150382675337481 --9.0,0.1504301874457461,2.6166544368792525e-21,-0.6371323632116463,0.1982607529225381 --8.5,0.1386276524536477,2.450570716745941e-21,-0.583498032661642,0.182046261914037 --8.0,0.1275294962908461,2.28945191394842e-21,-0.5315122916143107,0.1663960996351372 --7.5,0.1171754709784478,2.133272416176612e-21,-0.4811686704299467,0.1513115712127311 --7.0,0.10760532853756,1.9820066111204418e-21,-0.4324606994688453,0.1367939817737111 --6.5,0.0988588209892892,1.835628886469833e-21,-0.3853819090913009,0.1228446364449695 --6.0,0.0909757003547424,1.694113629914708e-21,-0.3399258296576083,0.1094648403533986 --5.5,0.0839957186550263,1.557435229144991e-21,-0.2960859915280623,0.096655898625891 --5.0,0.0779586279112478,1.4255680718506053e-21,-0.2538559250629577,0.0844191163893389 --4.5,0.0727676807943206,1.304392579507697e-21,-0.2159550434674728,0.0730550516548853 --4.0,0.0682091846241277,1.1952100521496464e-21,-0.1829588587323138,0.0626174354043963 --3.5,0.0641474733952293,1.0911261953022305e-21,-0.1516450493960662,0.0527373322208485 --3.0,0.0604468811021856,9.852467144912246e-22,-0.1187912939973158,0.0430458066872185 --2.5,0.0569717417395568,8.706773152424055e-22,-0.0811752710746482,0.0331739233864828 --2.0,0.0535863893019032,7.405237030815496e-22,-0.0355746591666493,0.0227527469016182 --1.5,0.0503504235725568,5.856067102929198e-22,0.0262260997508276,0.0114814493008274 --1.0,0.0473577829911575,4.092358225858232e-22,0.1042908628198079,-0.0002656553047875 --0.5,0.0445243095367264,2.232497256236004e-22,0.189614400178524,-0.0118447892679018 -0.0,0.0417658451882849,3.948710506959264e-23,0.2731914819652083,-0.0226121749411904 -0.5,0.0389381585076991,-1.5308243840478701e-22,0.3557444890017091,-0.0333669989367228 -1.0,0.0361177702917579,-3.560898065690111e-22,0.4410912179803868,-0.0442048470204237 -1.5,0.0335516508718663,-5.435970674210673e-22,0.5248695628452424,-0.0534265402757499 -2.0,0.0314867705794295,-6.896662889589436e-22,0.6027174175402769,-0.0593328997861588 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-24.5,0.3859564070240353,-7.24876347378319e-22,1.0536899775400672,-0.1830703298722823 diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD/2.csv b/data/TUDELFT_V3_KITE/2D_polars_CFD/2.csv deleted file mode 100644 index 7bf14858..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/2.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.1028496958630713,-4.970266483175547e-24,-0.4060358502753723,0.0550990480582689 --9.5,0.0971839746448208,-9.302148562803722e-24,-0.4438529313194241,0.0537303438488007 --9.0,0.0916177006701586,-2.1982895735540862e-23,-0.4741345054395691,0.0511424232336705 --8.5,0.0861488323939917,-4.2540159402165874e-23,-0.4977178511829077,0.047464579144667 --8.0,0.0807753282712272,-7.050159096345767e-23,-0.5154402470965408,0.0428261045135789 --7.5,0.0754951467567722,-1.0539484182019521e-22,-0.5281389717275694,0.0373562922721951 --7.0,0.070306246305534,-1.4674756337315738e-22,-0.536651303623094,0.0311844353523042 --6.5,0.0652065853724195,-1.9408740702312298e-22,-0.5418145213302155,0.0244398266856952 --6.0,0.0601941224123359,-2.4694202417087115e-22,-0.5444659033960346,0.0172517592041566 --5.5,0.0552668158801903,-3.048390662171807e-22,-0.5454427283676522,0.0097495258394774 --5.0,0.0504226242308899,-3.6730618456283053e-22,-0.5455822747921689,0.0020624195234464 --4.5,0.0454586930290803,-4.8527727098003185e-22,-0.5164772120836574,-0.0086109691796144 --4.0,0.0403444322748116,-6.841919162753791e-22,-0.4407589545148366,-0.0234630209344745 --3.5,0.0353361970760969,-9.25336320401227e-22,-0.3358228979207768,-0.0399508996529828 --3.0,0.0306903425409498,-1.1699966833099293e-21,-0.2190644381365483,-0.0555317692469881 --2.5,0.0266632237773835,-1.379459204953841e-21,-0.1078789709972217,-0.0676627936283392 --2.0,0.0235111958934114,-1.5150100852853154e-21,-0.0196618923378672,-0.0738011367088848 --1.5,0.0209681290308454,-1.593094370401261e-21,0.0469798152131813,-0.0758613643823688 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-21.0,0.2887815618087863,-2.942086719299423e-21,0.5716159082239023,-0.2609884237215353 -21.5,0.2950112400062896,-3.101798349276385e-21,0.5307305314004064,-0.2742269362348293 -22.0,0.3002894608295286,-3.2702615997103588e-21,0.4890725408751303,-0.287932096489727 -22.5,0.304535413794256,-3.447466928046934e-21,0.4466151760167164,-0.3021139784395067 -23.0,0.3076682884162247,-3.633404791731706e-21,0.4033316761938067,-0.316782656037447 -23.5,0.3096072742111871,-3.828065648210263e-21,0.3591952807750433,-0.3319482032368263 -24.0,0.3102715606948962,-4.031439954928197e-21,0.3141792291290685,-0.3476206939909228 -24.5,0.3095803373831047,-4.2435181693311005e-21,0.2682567606245242,-0.3638102022530151 diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD/3.csv b/data/TUDELFT_V3_KITE/2D_polars_CFD/3.csv deleted file mode 100644 index 9da21f4f..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/3.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.1173361087348235,-5.7736750521880425e-22,-0.3582621464079576,0.0656443151844469 --9.5,0.108551107621824,-5.433183423918373e-22,-0.3212594091978243,0.0656463154162551 --9.0,0.1002287848530749,-5.1605388359681195e-22,-0.2909643828536245,0.0656524678131497 --8.5,0.0924779724164097,-4.948202728301795e-22,-0.2667145752427244,0.0656629999273352 --8.0,0.0854075022996621,-4.788636540883907e-22,-0.24784749423249,0.0656781393110163 --7.5,0.0791262064906656,-4.6743017136789625e-22,-0.2337006476902874,0.0656981135163974 --7.0,0.0737429169772538,-4.597659686651472e-22,-0.2236115434834825,0.0657231500956833 --6.5,0.0693664657472603,-4.551171899765944e-22,-0.2169176894794415,0.0657534766010785 --6.0,0.0661056847885185,-4.527299792986889e-22,-0.2129565935455305,0.0657893205847876 --5.5,0.0640694060888622,-4.518504806278818e-22,-0.2110657635491154,0.0658309095990153 --5.0,0.0633664616361249,-4.517248379606235e-22,-0.2105827073575624,0.0658784711959661 --4.5,0.0635157916288774,-5.072753009721692e-22,-0.2223725843412344,0.0672530541907731 --4.0,0.0638891166107589,-6.461514585010337e-22,-0.2518472768004147,0.0706114667467596 --3.5,0.0643744390872047,-8.266904632885572e-22,-0.290164376997349,0.0749575754384152 --3.0,0.0648597615636506,-1.007229468076081e-21,-0.3284814771942833,0.0792952468402296 --2.5,0.065233086545532,-1.1461056256049454e-21,-0.3579561696534635,0.0826283475266925 --2.0,0.0653824165382846,-1.201656088616491e-21,-0.3697460466371356,0.0839607440722936 --1.5,0.062881700691689,-1.1710167119960766e-21,-0.3332643602791358,0.0760714433536522 --1.0,0.0569710144783453,-1.092122721455453e-21,-0.2441950052654193,0.057342231803168 --0.5,0.0500375498879175,-9.845103259755489e-22,-0.1331015376864097,0.0351811453290011 -0.0,0.04446849891007,-8.677157345372933e-22,-0.0305475136325313,0.0169962198393114 -0.5,0.0404275191138051,-7.21552828034642e-22,0.0612869819830996,0.0029319572058106 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a/data/TUDELFT_V3_KITE/2D_polars_CFD/5.csv b/data/TUDELFT_V3_KITE/2D_polars_CFD/5.csv deleted file mode 100644 index 0e9a5619..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/5.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.0940982450065733,-6.6387574576228175e-22,-0.2305337232124537,0.0463326586318861 --9.5,0.0858344424224717,-6.254029935251643e-22,-0.1850458799185888,0.0411226874800112 --9.0,0.0781658310151874,-5.915254158650829e-22,-0.1467431651766269,0.0369508655613513 --8.5,0.0711571087947452,-5.621145481643996e-22,-0.1150610117646866,0.0337018429611047 --8.0,0.06487297377117,-5.37041925805477e-22,-0.0894348524608866,0.0312602697644696 --7.5,0.0593781239544869,-5.161790841706766e-22,-0.0693001200433456,0.0295107960566445 --7.0,0.0547372573547205,-4.993975586423611e-22,-0.0540922472901822,0.0283380719228276 --6.5,0.051015071981896,-4.865688846028927e-22,-0.0432466669795152,0.0276267474482174 --6.0,0.0482762658460381,-4.775645974346335e-22,-0.0361988118894633,0.0272614727180122 --5.5,0.0465855369571717,-4.722562325199457e-22,-0.0323841147981451,0.0271268978174102 --5.0,0.0460075833253219,-4.7051532524119145e-22,-0.0312380084836793,0.02710767283161 --4.5,0.0465232097402304,-4.77194146738202e-22,-0.0432437279505954,0.0292075390704142 --4.0,0.0478122757775019,-4.938912004807278e-22,-0.0732580266178859,0.0344572046674247 --3.5,0.0494880616259549,-5.155973703460114e-22,-0.1122766148853635,0.0412817699435383 --3.0,0.0511638474744078,-5.373035402112951e-22,-0.1512952031528411,0.048106335219652 --2.5,0.0524529135116793,-5.54000593953821e-22,-0.1813095018201316,0.0533560008166625 --2.0,0.0529685399265879,-5.6067941545083135e-22,-0.1933152212870478,0.0554558670554667 --1.5,0.0522092299644608,-5.463094868753852e-22,-0.1741297686074671,0.0513823416282602 --1.0,0.0501672808379414,-5.070907610326474e-22,-0.1220119049109158,0.0406203957840108 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--9.5,0.1326841471304602,-4.75417641596303e-22,-0.4065829051789078,0.0680801363138168 --9.0,0.12734677769483,-4.709684480026902e-22,-0.4023810830160209,0.0686076868842134 --8.5,0.1219631811545753,-4.637104125637368e-22,-0.3956680909459696,0.0690185442408817 --8.0,0.1165354163130465,-4.537722248206797e-22,-0.3866812384062852,0.0693272950355378 --7.5,0.1110655419735937,-4.412825743147561e-22,-0.3756578348344989,0.0695485259198976 --7.0,0.1055556169395673,-4.263701505872032e-22,-0.3628351896681416,0.0696968235456773 --6.5,0.1000077000143173,-4.0916364317925823e-22,-0.3484506123447448,0.0697867745645929 --6.0,0.0944238500011941,-3.897917416321581e-22,-0.3327414123018395,0.0698329656283603 --5.5,0.0888061257035479,-3.683831354871403e-22,-0.3159448989769569,0.0698499833886957 --5.0,0.0831565859247289,-3.4506651428544187e-22,-0.2982983818076282,0.0698524144973151 --4.5,0.0771151789292091,-3.046810902143808e-22,-0.2750532835401525,0.0680649176687529 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-23.5,0.9541104954051636,1.0759568323181111e-20,3.957278679463312,0.326198362509867 -24.0,1.008953035807942,1.2279514698849225e-20,4.528494173686367,0.5000017536286244 -24.5,1.0158348333797813,1.3511352646122724e-20,4.974044854808042,0.6852234084181389 diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD/7.csv b/data/TUDELFT_V3_KITE/2D_polars_CFD/7.csv deleted file mode 100644 index a47b9814..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/7.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.1262828136989528,-8.90890973272729e-22,-0.3618057217093356,0.0652837657478573 --9.5,0.1130428852156888,-8.005712992452283e-22,-0.2848783004875012,0.0546633765377905 --9.0,0.1006975445583256,-7.232286273831203e-22,-0.2192507168674447,0.0460781560034993 --8.5,0.0893643457137361,-6.580457218216844e-22,-0.1641687302873054,0.0393120616687077 --8.0,0.0791608426687932,-6.042053466962e-22,-0.1188781001852222,0.0341490510571395 --7.5,0.0702045894103697,-5.608902661419464e-22,-0.0826245859993343,0.0303730816925187 --7.0,0.0626131399253385,-5.272832442942032e-22,-0.0546539471677809,0.0277681110985693 --6.5,0.0565040482005725,-5.0256704528825e-22,-0.0342119431287008,0.0261180967990151 --6.0,0.0519948682229447,-4.85924433259366e-22,-0.0205443333202333,0.0252069963175801 --5.5,0.0492031539793279,-4.765381723428306e-22,-0.0128968771805174,0.0248187671779882 --5.0,0.048246459456595,-4.735910266739232e-22,-0.0105153341476925,0.0247373669039634 --4.5,0.0489341964660458,-4.9440478364657945e-22,-0.0288222252158359,0.0283791076289984 --4.0,0.0506535389896728,-5.4643917607822e-22,-0.0745894528861945,0.0374834594415859 --3.5,0.052888684270388,-6.140838862393528e-22,-0.1340868488576607,0.0493191167979498 --3.0,0.0551238295511032,-6.817285964004857e-22,-0.1935842448291269,0.0611547741543136 --2.5,0.0568431720747302,-7.337629888321259e-22,-0.2393514724994855,0.0702591259669011 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d62c4be0..00000000 --- a/data/TUDELFT_V3_KITE/2D_polars_CFD/8.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.1145642577313759,-1.0186945209532765e-21,-0.2989604670437933,0.0581854929136097 --9.5,0.1021311837448767,-9.918217508383414e-22,-0.2245458665019229,0.048341941984193 --9.0,0.0906909354995368,-9.703037024437254e-22,-0.162273921099489,0.0404598366274276 --8.5,0.0803179236427649,-9.535454066893933e-22,-0.1111295740608856,0.0343212384463522 --8.0,0.0710865588219696,-9.409518944953092e-22,-0.0700977686105066,0.0297082090440056 --7.5,0.0630712516845598,-9.319281967814382e-22,-0.038163447972746,0.0264028100234266 --7.0,0.0563464128779443,-9.258793444677441e-22,-0.0143115553719979,0.0241871029876538 --6.5,0.0509864530495317,-9.22210368474192e-22,0.0024729659673437,0.0228431495397261 --6.0,0.047065782846731,-9.203262997207466e-22,0.0132051728208852,0.0221530112826821 --5.5,0.0446588129169508,-9.196321691273718e-22,0.0189001219642324,0.0218987498195607 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a/data/TUDELFT_V3_KITE/geometry.yaml b/data/TUDELFT_V3_KITE/geometry_CAD_CFD_polars_pchip_fitted.yaml similarity index 50% rename from data/TUDELFT_V3_KITE/geometry.yaml rename to data/TUDELFT_V3_KITE/geometry_CAD_CFD_polars_pchip_fitted.yaml index 7789868a..a8e2612f 100644 --- a/data/TUDELFT_V3_KITE/geometry.yaml +++ b/data/TUDELFT_V3_KITE/geometry_CAD_CFD_polars_pchip_fitted.yaml @@ -11,43 +11,43 @@ wing_sections: # --------------------------------------------------------------- headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] data: - - [19, 0.10494809354160103, 4.110425010287237, 1.0206948819027293, 0.9322352740642089, 4.136759541813347, 1.0267698564834051] - - [18,-0.12594856150986303, 4.095312460948618, 1.131752674216157, 0.9480319715306028, 4.119176793915081, 1.1375068826415087] - - [17,-0.415204088177974, 4.058392218797549, 1.3527398161728057, 0.9806642670037444, 4.0661917809302714, 1.354784652851428] - - [16,-0.5839406178913704, 4.017404143963288, 1.573136130673558, 1.0133061573517872, 4.0126965083918655, 1.5718020624211284] - - [15,-0.6731255454312801, 3.9710648600916856, 1.792296994306359, 1.0459407519807051, 3.959304771307195, 1.788711553698102] - - [14,-0.7630010692513897, 3.808661454565653, 2.2116503076074623, 1.1148900094481449, 3.8099544198423287, 2.212462687618386] - - [13,-0.8034346573868656, 3.671721332477886, 2.3902080961084446, 1.1590484514963157, 3.676560321852442, 2.394355401152323] - - [12,-0.8426236438512831, 3.5037765531662273, 2.5431468790470166, 1.2069146554234733, 3.5081098865401383, 2.54813951074277] - - [11,-0.9107041725649544, 3.136094612354681, 2.798744478912709, 1.3282999037052468, 3.1343435230977734, 2.7965040693723457] - - [10,-0.9734084029764644, 2.799119438334862, 3.0942397365885954, 1.341651389866222, 2.7979060165852596, 3.0924012745521683] - - [9, -1.0012604181004636, 2.60606743950073, 3.2109156756433377, 1.3470535121521396, 2.607652208222479, 3.2140730423076005] - - [8, -1.0255704673876633, 2.3933957820040352, 3.2892227589446676, 1.3704766336634273, 2.3946575320852, 3.292717092764685] - - [7, -1.066808167099677, 1.9597511829533572, 3.398710571788576, 1.4286937460004634, 1.9587427796536303, 3.395858306351975] - - [6, -1.102721455861017, 1.5539231291222366, 3.587899390284646, 1.4218476587327253, 1.5529087742581646, 3.5847357425519175] - - [5, -1.1174483964012778, 1.3372547196154843, 3.6531307248857057, 1.4206278262933396, 1.337221665561774, 3.652962868560538] - - [4, -1.1290037004055944, 1.111273134975715, 3.672140965756021, 1.4350857915331694, 1.1111744842343718, 3.670881486234418] - - [3, -1.1448828836323988, 0.6642030404518473, 3.658203792543517, 1.4733964618305042, 0.6638228115665804, 3.653361447444984] - - [2, -1.1544229650457856, 0.22477286325409476, 3.739264150331224, 1.4484005139953104, 0.2247570459738744, 3.7390964622164637] - - [1, -1.1557911914860979, 0.0, 3.7549161879983592, 1.443146003226444, 0.0, 3.754972573823276] - - [2, -1.1544229650457856, -0.22477286325409476, 3.739264150331224, 1.4484005139953104, -0.2247570459738744, 3.7390964622164637] - - [3, -1.1448828836323988, -0.6642030404518473, 3.658203792543517, 1.4733964618305042, -0.6638228115665804, 3.653361447444984] - - [4, -1.1290037004055944, -1.111273134975715, 3.672140965756021, 1.4350857915331694, -1.1111744842343718, 3.670881486234418] - - [5, -1.1174483964012778, -1.3372547196154843, 3.6531307248857057, 1.4206278262933396, -1.337221665561774, 3.652962868560538] - - [6, -1.102721455861017, -1.5539231291222366, 3.587899390284646, 1.4218476587327253, -1.5529087742581646, 3.5847357425519175] - - [7, -1.066808167099677, -1.9597511829533572, 3.398710571788576, 1.4286937460004634, -1.9587427796536303, 3.395858306351975] - - [8, -1.0255704673876633, -2.3933957820040352, 3.2892227589446676, 1.3704766336634273, -2.3946575320852, 3.292717092764685] - - [9, -1.0012604181004636, -2.60606743950073, 3.2109156756433377, 1.3470535121521396, -2.607652208222479, 3.2140730423076005] - - [10,-0.9734084029764644, -2.799119438334862, 3.0942397365885954, 1.341651389866222, -2.7979060165852596, 3.0924012745521683] - - [11,-0.9107041725649544, -3.136094612354681, 2.798744478912709, 1.3282999037052468, -3.1343435230977734, 2.7965040693723457] - - [12,-0.8426236438512831, -3.5037765531662273, 2.5431468790470166, 1.2069146554234733, -3.5081098865401383, 2.54813951074277] - - [13,-0.8034346573868656, -3.671721332477886, 2.3902080961084446, 1.1590484514963157, -3.676560321852442, 2.394355401152323] - - [14,-0.7630010692513897, -3.808661454565653, 2.2116503076074623, 1.1148900094481449, -3.8099544198423287, 2.212462687618386] - - [15,-0.6731255454312801, -3.9710648600916856, 1.792296994306359, 1.0459407519807051, -3.959304771307195, 1.788711553698102] - - [16,-0.5839406178913704, -4.017404143963288, 1.573136130673558, 1.0133061573517872, -4.0126965083918655, 1.5718020624211284] - - [17,-0.415204088177974, -4.058392218797549, 1.3527398161728057, 0.9806642670037444, -4.0661917809302714, 1.354784652851428] - - [18,-0.12594856150986303, -4.095312460948618, 1.131752674216157, 0.9480319715306028, -4.119176793915081, 1.1375068826415087] - - [19, 0.10494809354160103, -4.110425010287237, 1.0206948819027293, 0.9322352740642089, -4.136759541813347, 1.0267698564834051] + - [19, 0.10494809354160103, 4.110425010287237, 8.27069488190273, 0.9322352740642089, 4.136759541813347, 8.276769856483405] + - [18, -0.12594856150986303, 4.095312460948618, 8.381752674216157, 0.9480319715306028, 4.119176793915081, 8.387506882641508] + - [17, -0.415204088177974, 4.058392218797549, 8.602739816172805, 0.9806642670037444, 4.0661917809302714, 8.604784652851428] + - [16, -0.5839406178913704, 4.017404143963288, 8.823136130673557, 1.0133061573517872, 4.0126965083918655, 8.821802062421128] + - [15, -0.6731255454312801, 3.9710648600916856, 9.042296994306358, 1.0459407519807051, 3.959304771307195, 9.038711553698102] + - [14, -0.7630010692513897, 3.808661454565653, 9.461650307607462, 1.1148900094481449, 3.8099544198423287, 9.462462687618386] + - [13, -0.8034346573868656, 3.671721332477886, 9.640208096108445, 1.1590484514963157, 3.676560321852442, 9.644355401152323] + - [12, -0.8426236438512831, 3.5037765531662273, 9.793146879047017, 1.2069146554234733, 3.5081098865401383, 9.79813951074277] + - [11, -0.9107041725649544, 3.136094612354681, 10.04874447891271, 1.3282999037052468, 3.1343435230977734, 10.046504069372347] + - [10, -0.9734084029764644, 2.799119438334862, 10.344239736588595, 1.341651389866222, 2.7979060165852596, 10.342401274552168] + - [9, -1.0012604181004636, 2.60606743950073, 10.460915675643339, 1.3470535121521396, 2.607652208222479, 10.4640730423076] + - [8, -1.0255704673876633, 2.3933957820040352, 10.539222758944668, 1.3704766336634273, 2.3946575320852, 10.542717092764684] + - [7, -1.066808167099677, 1.9597511829533572, 10.648710571788577, 1.4286937460004634, 1.9587427796536303, 10.645858306351975] + - [6, -1.102721455861017, 1.5539231291222366, 10.837899390284646, 1.4218476587327253, 1.5529087742581646, 10.834735742551917] + - [5, -1.1174483964012778, 1.3372547196154843, 10.903130724885706, 1.4206278262933396, 1.337221665561774, 10.902962868560538] + - [4, -1.1290037004055944, 1.111273134975715, 10.922140965756022, 1.4350857915331694, 1.1111744842343718, 10.920881486234418] + - [3, -1.1448828836323988, 0.6642030404518473, 10.908203792543517, 1.4733964618305042, 0.6638228115665804, 10.903361447444984] + - [2, -1.1544229650457856, 0.22477286325409476, 10.989264150331223, 1.4484005139953104, 0.2247570459738744, 10.989096462216464] + - [1, -1.1557911914860979, 0.0, 11.00491618799836, 1.443146003226444, 0.0, 11.004972573823276] + - [2, -1.1544229650457856, -0.22477286325409476, 10.989264150331223, 1.4484005139953104, -0.2247570459738744, 10.989096462216464] + - [3, -1.1448828836323988, -0.6642030404518473, 10.908203792543517, 1.4733964618305042, -0.6638228115665804, 10.903361447444984] + - [4, -1.1290037004055944, -1.111273134975715, 10.922140965756022, 1.4350857915331694, -1.1111744842343718, 10.920881486234418] + - [5, -1.1174483964012778, -1.3372547196154843, 10.903130724885706, 1.4206278262933396, -1.337221665561774, 10.902962868560538] + - [6, -1.102721455861017, -1.5539231291222366, 10.837899390284646, 1.4218476587327253, -1.5529087742581646, 10.834735742551917] + - [7, -1.066808167099677, -1.9597511829533572, 10.648710571788577, 1.4286937460004634, -1.9587427796536303, 10.645858306351975] + - [8, -1.0255704673876633, -2.3933957820040352, 10.539222758944668, 1.3704766336634273, -2.3946575320852, 10.542717092764684] + - [9, -1.0012604181004636, -2.60606743950073, 10.460915675643339, 1.3470535121521396, -2.607652208222479, 10.4640730423076] + - [10, -0.9734084029764644, -2.799119438334862, 10.344239736588595, 1.341651389866222, -2.7979060165852596, 10.342401274552168] + - [11, -0.9107041725649544, -3.136094612354681, 10.04874447891271, 1.3282999037052468, -3.1343435230977734, 10.046504069372347] + - [12, -0.8426236438512831, -3.5037765531662273, 9.793146879047017, 1.2069146554234733, -3.5081098865401383, 9.79813951074277] + - [13, -0.8034346573868656, -3.671721332477886, 9.640208096108445, 1.1590484514963157, -3.676560321852442, 9.644355401152323] + - [14, -0.7630010692513897, -3.808661454565653, 9.461650307607462, 1.1148900094481449, -3.8099544198423287, 9.462462687618386] + - [15, -0.6731255454312801, -3.9710648600916856, 9.042296994306358, 1.0459407519807051, -3.959304771307195, 9.038711553698102] + - [16, -0.5839406178913704, -4.017404143963288, 8.823136130673557, 1.0133061573517872, -4.0126965083918655, 8.821802062421128] + - [17, -0.415204088177974, -4.058392218797549, 8.602739816172805, 0.9806642670037444, -4.0661917809302714, 8.604784652851428] + - [18, -0.12594856150986303, -4.095312460948618, 8.381752674216157, 0.9480319715306028, -4.119176793915081, 8.387506882641508] + - [19, 0.10494809354160103, -4.110425010287237, 8.27069488190273, 0.9322352740642089, -4.136759541813347, 8.276769856483405] wing_airfoils: # --------------------------------------------------------------- @@ -83,25 +83,25 @@ wing_airfoils: reynolds: !!float 1e6 # Reynolds number headers: [airfoil_id, type, info_dict] data: - - [1, polars, {csv_file_path: "2D_polars_CFD/1.csv"}] - - [2, polars, {csv_file_path: "2D_polars_CFD/2.csv"}] - - [3, polars, {csv_file_path: "2D_polars_CFD/3.csv"}] - - [4, polars, {csv_file_path: "2D_polars_CFD/4.csv"}] - - [5, polars, {csv_file_path: "2D_polars_CFD/5.csv"}] - - [6, polars, {csv_file_path: "2D_polars_CFD/6.csv"}] - - [7, polars, {csv_file_path: "2D_polars_CFD/7.csv"}] - - [8, polars, {csv_file_path: "2D_polars_CFD/8.csv"}] - - [9, polars, {csv_file_path: "2D_polars_CFD/9.csv"}] - - [10, polars, {csv_file_path: "2D_polars_CFD/10.csv"}] - - [11, polars, {csv_file_path: "2D_polars_CFD/11.csv"}] - - [12, polars, {csv_file_path: "2D_polars_CFD/12.csv"}] - - [13, polars, {csv_file_path: "2D_polars_CFD/13.csv"}] - - [14, polars, {csv_file_path: "2D_polars_CFD/14.csv"}] - - [15, polars, {csv_file_path: "2D_polars_CFD/15.csv"}] - - [16, polars, {csv_file_path: "2D_polars_CFD/16.csv"}] - - [17, polars, {csv_file_path: "2D_polars_CFD/17.csv"}] - - [18, polars, {csv_file_path: "2D_polars_CFD/18.csv"}] - - [19, polars, {csv_file_path: "2D_polars_CFD/19.csv"}] + - [1, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/1.csv"}] + - [2, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/2.csv"}] + - [3, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/3.csv"}] + - [4, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/4.csv"}] + - [5, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/5.csv"}] + - [6, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/6.csv"}] + - [7, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/7.csv"}] + - [8, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/8.csv"}] + - [9, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/9.csv"}] + - [10, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/10.csv"}] + - [11, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/11.csv"}] + - [12, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/12.csv"}] + - [13, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/13.csv"}] + - [14, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/14.csv"}] + - [15, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/15.csv"}] + - [16, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/16.csv"}] + - [17, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/17.csv"}] + - [18, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/18.csv"}] + - [19, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/19.csv"}] @@ -227,3 +227,4 @@ bridle_connections: + diff --git a/data/TUDELFT_V3_KITE/literature_results/Python_VSM_Rey_5e5_n36_CFD_PCHIP_polars_alpha_sweep.csv b/data/TUDELFT_V3_KITE/literature_results/Python_VSM_Rey_5e5_n36_CFD_PCHIP_polars_alpha_sweep.csv new file mode 100644 index 00000000..b6f0c626 --- /dev/null +++ b/data/TUDELFT_V3_KITE/literature_results/Python_VSM_Rey_5e5_n36_CFD_PCHIP_polars_alpha_sweep.csv @@ -0,0 +1,63 @@ +alpha,CL,CD,CS,CMx,CMy,CMz +-5.0,-0.016639150841432696,0.06461257742824286,8.478187720501367e-17,-3.061887882386819e-16,0.28227103088648064,3.1640606750175953e-17 +-4.508196721311475,-0.15116141710337438,0.06813042331168648,1.6558287946512188e-16,-4.3472875316127167e-16,0.2448193040108129,2.741773931281523e-17 +-4.016393442622951,-0.12359435503424275,0.06467079023399522,2.22928996914706e-16,-5.896358903756748e-16,0.24394876629214812,1.3945762219966873e-17 +-3.5245901639344264,-0.0955075625757297,0.06140805998980694,2.3960563519741807e-16,-6.054561937507627e-16,0.2420546192298006,1.9095600558211657e-17 +-3.0327868852459017,-0.08614032786011963,0.059727576261926124,2.560670910506758e-16,-6.24901983315975e-16,0.24100968398007022,2.597578457810669e-17 +-2.540983606557377,-0.0552050539665637,0.05704706679467209,3.208907979237986e-16,-8.223261858509271e-16,0.23846691212426813,3.934476490419015e-17 +-2.0491803278688527,-0.023671564731756238,0.054662724982745055,2.9679036582491142e-16,-7.499812568752643e-16,0.23501881516673262,2.978666494840783e-17 +-1.557377049180328,0.008844196939017434,0.05251409193106237,3.002063868924993e-16,-7.601161387249302e-16,0.23045212739790363,2.5090012383928592e-17 +-1.0655737704918034,0.0415747891970653,0.05060381840435065,2.890169005608731e-16,-7.430804735020164e-16,0.22471056723584462,1.614989302873564e-17 +-0.5737704918032787,0.07502466254074833,0.04891798700234494,3.0738810047553817e-16,-7.754008589128406e-16,0.2177951282212764,2.830351150699333e-17 +-0.08196721311475397,0.10889694335333432,0.047464944609758454,2.84202193701832e-16,-7.096065243034252e-16,0.20978226669304198,2.2494493861453216e-17 +0.4098360655737707,0.14309203022027436,0.04622054569950249,2.4401687500123214e-16,-5.785946369784777e-16,0.20048986627783982,1.1103051457255748e-17 +0.9016393442622945,0.1780413579153343,0.04526384343079455,2.669338037381205e-16,-7.267451862931039e-16,0.19045131694925846,2.0985591228347496e-17 +1.3934426229508192,0.21395263479636484,0.04447997622080856,2.912494182664618e-16,-8.450678719526157e-16,0.17884135671129764,1.8766010904563983e-17 +1.885245901639344,0.250813572958965,0.04389188664361113,1.9097440614073512e-16,-4.643918219895616e-16,0.16568961707932453,1.408995769343773e-17 +2.3770491803278686,0.28895949644132035,0.04350125508066167,4.0626442680981155e-16,-1.014476953927516e-15,0.1508258269234812,4.0539527398662916e-17 +2.8688524590163933,0.3273497069332273,0.04329404509617653,1.2824872795479226e-16,-3.203611433455315e-16,0.1341391252119524,3.275297183123682e-17 +3.360655737704917,0.365700349792079,0.04337836667220271,1.9990447696309065e-16,-4.080319912158108e-16,0.11648263639587733,1.936339215180039e-17 +3.8524590163934427,0.40370330464829807,0.04368762204422157,2.816738001557434e-16,-7.916743480616941e-16,0.09735955183971143,1.9610584392036138e-17 +4.3442622950819665,0.4404116927505139,0.044306322502976996,1.6375382881475996e-16,-3.8232399823129283e-16,0.07791841285021213,2.315367316874855e-17 +4.836065573770492,0.4762504901989163,0.04515131620054717,2.369158548292387e-16,-6.24901983315975e-16,0.057514814009507295,2.0764148179802968e-17 +5.327868852459016,0.5109687991364886,0.04622052439565633,9.209807980646155e-17,-4.073728119085154e-16,0.03637335615544438,2.19177119675698e-17 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[kg/m^3] Air density at sea level + project_dir = dirname(dirname(pathof(VortexStepMethod))) # Go up one level from src to project root -yaml_geometry_path = joinpath(project_dir, "data", "TUDELFT_V3_KITE", "geometry.yaml") +yaml_geometry_path = joinpath(project_dir, "data", "TUDELFT_V3_KITE", "geometry_CAD_CFD_polars_pchip_fitted.yaml") literature_paths = [ - # joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv"), - # joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv"), - joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","Python_VSM_Rey_5e5_Poland2025_alpha_sweep_beta_0.csv"), - # joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","WindTunnel_Re_5e5_Poland2025_alpha_sweep_beta_0.csv") + joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv"), + joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv"), + joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","Python_VSM_Rey_5e5_n36_CFD_PCHIP_polars_alpha_sweep.csv"), + joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","WindTunnel_Re_5e5_Poland2025_alpha_sweep_beta_0.csv"), ] labels= [ - "VSM Julia", - # "CFD RANS Re=5e5", - # "CFD RANS Re=10e5", - "Python VSM Re=5e5", - # "Wind Tunnel Re=5e5" + "Julia VSM 2D CFD PCHIP", + "CFD RANS Re=5e5", + "CFD RANS Re=10e5", + "Python VSM 2D CFD PCHIP Re=5e5", + "Wind Tunnel Re=5e5" ] -# println("=== Static Aerodynamic Analysis (VSM) ===") -# println("Wind speed: $wind_speed m/s") -# println("Angle of attack: $angle_of_attack_deg deg") -# println("Sideslip: $sideslip_deg deg") - # Create wing, body_aero, and solver objects -wing = YamlWing(yaml_geometry_path; n_panels=40, spanwise_distribution=LINEAR) +wing = YamlWing(yaml_geometry_path; n_panels=36, spanwise_distribution=LINEAR) body_aero = BodyAerodynamics([wing]) solver = Solver(body_aero; aerodynamic_model_type=VSM, is_with_artificial_damping=false, - rtol=1e-5, - solver_type=NONLIN + solver_type=LOOP, + density=1.225, + max_iterations=5000, + rtol = 1e-6, + relaxation_factor=0.01, + core_radius_fraction=1e-20, ) # Using plotting modules, to create more comprehensive plots PLOT = true USE_TEX = false - # Plotting polars PLOT && plot_polars( [solver], [body_aero], labels, literature_path_list=literature_paths, - angle_range=range(5, 10, length=2), + angle_range=range(1, 20, length=20), angle_type="angle_of_attack", angle_of_attack=angle_of_attack_deg, side_slip=sideslip_deg, @@ -63,44 +61,44 @@ PLOT && plot_polars( ) -# # Plotting geometry -# --- Set apparent wind vector in body axes --- -# α = deg2rad(angle_of_attack_deg) -# β = deg2rad(sideslip_deg) -# va = wind_speed * [ -# cos(α)*cos(β), # X_b (forward) -# sin(β), # Y_b (right) -# sin(α)*cos(β) # Z_b (down) -# ] -# set_va!(body_aero, va) +# Plotting geometry +#--- Set apparent wind vector in body axes --- +α = deg2rad(angle_of_attack_deg) +β = deg2rad(sideslip_deg) +va = wind_speed * [ + cos(α)*cos(β), # X_b (forward) + sin(β), # Y_b (right) + sin(α)*cos(β) # Z_b (down) +] +set_va!(body_aero, va) -# results = VortexStepMethod.solve(solver, body_aero; log=true) -# PLOT && plot_geometry( -# body_aero, -# ""; -# data_type=".svg", -# save_path="", -# is_save=false, -# is_show=true, -# view_elevation=15, -# view_azimuth=-120, -# use_tex=USE_TEX -# ) +results = VortexStepMethod.solve(solver, body_aero; log=true) +PLOT && plot_geometry( + body_aero, + ""; + data_type=".svg", + save_path="", + is_save=false, + is_show=true, + view_elevation=15, + view_azimuth=-120, + use_tex=USE_TEX +) -# # Plotting spanwise distributions -# body_y_coordinates = [panel.aero_center[2] for panel in body_aero.panels] +# Plotting spanwise distributions +body_y_coordinates = [panel.aero_center[2] for panel in body_aero.panels] -# PLOT && plot_distribution( -# [body_y_coordinates], -# [results], -# ["VSM"]; -# title="CAD_spanwise_distributions_alpha_$(round(angle_of_attack_deg, digits=1))_delta_$(round(sideslip_deg, digits=1))_yaw_$(round(yaw_rate, digits=1))_v_a_$(round(wind_speed, digits=1))", -# data_type=".pdf", -# is_save=false, -# is_show=true, -# use_tex=USE_TEX -# ) +PLOT && plot_distribution( + [body_y_coordinates], + [results], + ["VSM"]; + title="CAD_spanwise_distributions_alpha_$(round(angle_of_attack_deg, digits=1))_delta_$(round(sideslip_deg, digits=1))_yaw_$(round(yaw_rate, digits=1))_v_a_$(round(wind_speed, digits=1))", + data_type=".pdf", + is_save=false, + is_show=true, + use_tex=USE_TEX +) nothing \ No newline at end of file diff --git a/src/yaml_geometry.jl b/src/yaml_geometry.jl index 249afa49..d8242a38 100644 --- a/src/yaml_geometry.jl +++ b/src/yaml_geometry.jl @@ -1,3 +1,28 @@ +""" + @with_kw mutable struct AirfoilSettings + +Configuration settings for airfoils loaded from YAML files. + +This struct stores the mapping between airfoil IDs and their aerodynamic data sources, +typically CSV files containing polar data. It preserves the original YAML configuration +for reference and enables reconstruction of the wing geometry from YAML specifications. + +# Fields +- `airfoil_id::Int64`: Unique identifier for the airfoil section +- `type::String`: Type of aerodynamic data (e.g., "polars", "inviscid") +- `info_dict::Dict{String, Any}`: Additional configuration data, typically containing + file paths to CSV polar data files and other airfoil-specific parameters + +# Example +```julia +# Typical usage when parsing YAML wing configuration +settings = AirfoilSettings( + airfoil_id = 1, + type = "polars", + info_dict = Dict("csv_file_path" => "polars/airfoil_1.csv") +) +``` +""" @with_kw mutable struct AirfoilSettings airfoil_id::Int64 type::String @@ -21,8 +46,6 @@ A wing model created from YAML configuration files with CSV polar data. - `spanwise_distribution::PanelDistribution`: Panel distribution type - `sections::Vector{Section}`: Wing cross-sections with aerodynamic data - `airfoil_settings::Vector{AirfoilSettings}`: Airfoil configuration data -- `alpha_range::Vector{Float64}`: Angle of attack range for polars -- `reynolds::Float64`: Reynolds number for aerodynamic analysis See constructor `YamlWing(yaml_path; kwargs...)` for usage details. """ @@ -36,74 +59,19 @@ mutable struct YamlWing <: AbstractWing refined_sections::Vector{Section} remove_nan::Bool - # Additional fields for YamlWing + # Essential YAML-specific fields airfoil_settings::Vector{AirfoilSettings} - alpha_range::Vector{Float64} - reynolds::Float64 - cache::Vector{PreallocationTools.LazyBufferCache{typeof(identity), typeof(identity)}} end -# """ -# load_polar_data(csv_file_path) - -# Load polar data from CSV file at the given path. -# Expected CSV format: columns named alpha, cl, cd, cm (case insensitive) - -# Returns (aero_data, aero_model) tuple. -# """ -# function load_polar_data(csv_file_path::String) -# if isempty(csv_file_path) || !isfile(csv_file_path) -# @warn "Polar file not found or empty path: $csv_file_path. Using INVISCID model instead." -# return nothing, INVISCID -# end - -# try -# # Read the file and get headers -# file_content = readdlm(csv_file_path, ',') - -# # Extract headers (first row) and data (remaining rows) -# headers = String.(file_content[1, :]) -# data = file_content[2:end, :] -# # Get column names and find required columns (case insensitive) -# col_names_lower = lowercase.(headers) - -# # Find required columns by matching lowercase names -# alpha_col = findfirst(x -> x == "alpha", col_names_lower) -# cl_col = findfirst(x -> x == "cl", col_names_lower) -# cd_col = findfirst(x -> x == "cd", col_names_lower) -# cm_col = findfirst(x -> x == "cm", col_names_lower) - -# # Check if all required columns are found -# if isnothing(alpha_col) || isnothing(cl_col) || isnothing(cd_col) || isnothing(cm_col) -# missing_cols = String[] -# isnothing(alpha_col) && push!(missing_cols, "alpha") -# isnothing(cl_col) && push!(missing_cols, "cl") -# isnothing(cd_col) && push!(missing_cols, "cd") -# isnothing(cm_col) && push!(missing_cols, "cm") -# @warn "Missing columns $missing_cols in $csv_file_path. Using INVISCID model instead." -# return nothing, INVISCID -# end - -# # Extract data using column indices and convert to Float64 -# alpha_data = Float64.(data[:, alpha_col]) -# cl_data = Float64.(data[:, cl_col]) -# cd_data = Float64.(data[:, cd_col]) -# cm_data = Float64.(data[:, cm_col]) - -# # Create aero_data tuple -# aero_data = (alpha_data, cl_data, cd_data, cm_data) -# return aero_data, POLAR_VECTORS - -# catch e -# @warn "Error reading polar file $csv_file_path: $e. Using INVISCID model instead." -# return nothing, INVISCID -# end -# end """ load_polar_data(csv_file_path) Load polar data from a CSV file using only `readlines`. Expected format: header row and columns alpha, cl, cd, cm (case-insensitive, order arbitrary). +- alpha: Angle of attack in degrees +- cl: Lift coefficient +- cd: Drag coefficient +- cm: Moment coefficient Returns (aero_data, POLAR_VECTORS) or (nothing, INVISCID) if missing/invalid. """ @@ -133,8 +101,7 @@ function load_polar_data(csv_file_path::String) cd = Vector{Float64}(undef, n) cm = Vector{Float64}(undef, n) - # Converting to radians - alpha = deg2rad.(alpha) + # Read each data line for (i, line) in enumerate(lines[2:end]) @@ -144,6 +111,10 @@ function load_polar_data(csv_file_path::String) cd[i] = parse(Float64, fields[col_map["cd"]]) cm[i] = parse(Float64, fields[col_map["cm"]]) end + + # Converting to radians + alpha = deg2rad.(alpha) + return (alpha, cl, cd, cm), POLAR_VECTORS catch e @warn "Error reading polar file $csv_file_path: $e. Using INVISCID model instead." @@ -207,7 +178,7 @@ wing = YamlWing( function YamlWing( yaml_path; n_panels=20, - n_groups=4, + n_groups=1, spanwise_distribution=LINEAR, spanwise_direction=[0.0, 1.0, 0.0], remove_nan=true, @@ -260,14 +231,10 @@ function YamlWing( push!(refined_sections, Section(le_coord, te_coord, aero_model, aero_data)) end - # Extract configuration - alpha_range = get(yaml_data["wing_airfoils"], "alpha_range", [-10.0, 31.0, 0.5]) - reynolds = get(yaml_data["wing_airfoils"], "reynolds", 1e6) - # Create YamlWing YamlWing( n_panels, n_groups, spanwise_distribution, PanelProperties{n_panels}(), MVec3(spanwise_direction), sections, refined_sections, remove_nan, - airfoil_settings, alpha_range, reynolds, [LazyBufferCache()] + airfoil_settings ) end From 4d07971a3dcda2188872367f35bddee72b0bf12b Mon Sep 17 00:00:00 2001 From: jellepoland Date: Tue, 5 Aug 2025 11:38:53 +0200 Subject: [PATCH 10/26] #155 V3_kite example now creates wing and solver from VSMSettings --- data/TUDELFT_V3_KITE/vsm_settings.yaml | 121 +++++++++++++----- ...geometry_CAD_CFD_polars_pchip_fitted.yaml} | 0 examples/V3_kite.jl | 56 +++++--- src/settings.jl | 27 ++++ 4 files changed, 150 insertions(+), 54 deletions(-) rename data/TUDELFT_V3_KITE/{geometry_CAD_CFD_polars_pchip_fitted.yaml => wing_geometry_CAD_CFD_polars_pchip_fitted.yaml} (100%) diff --git a/data/TUDELFT_V3_KITE/vsm_settings.yaml b/data/TUDELFT_V3_KITE/vsm_settings.yaml index 5ae66dc9..09eb41fa 100644 --- a/data/TUDELFT_V3_KITE/vsm_settings.yaml +++ b/data/TUDELFT_V3_KITE/vsm_settings.yaml @@ -1,36 +1,91 @@ -Model: - VSM: Vortex Step Method - LLT: Lifting Line Theory -PanelDistribution: - LINEAR: Linear distribution - COSINE: Cosine distribution - COSINE_VAN_GARREL: van Garrel cosine distribution - SPLIT_PROVIDED: Split provided sections - UNCHANGED: Keep original sections -InitialGammaDistribution: - ELLIPTIC: Elliptic distribution - ZEROS: Constant distribution +# ============================================================================= +# VSM Settings Configuration File +# ============================================================================= +# +# This YAML file configures the Vortex Step Method (VSM) aerodynamic solver +# for wing analysis. All simulation parameters are centralized here. +# +# FILE STRUCTURE: +# ├── condition: Flight conditions (wind speed, angles, rates) +# ├── wings: Wing geometry and discretization settings +# └── solver_settings: Numerical solver parameters and convergence criteria +# +# AERODYNAMIC MODELS: +# VSM: Vortex Step Method - Full 3D potential flow with wake modeling +# LLT: Lifting Line Theory - Classical 1D approach for high aspect ratios +# +# PANEL DISTRIBUTIONS: +# LINEAR: Uniform panel spacing along wingspan +# COSINE: Cosine clustering (more panels at tips) +# COSINE_VAN_GARREL: Van Garrel's modified cosine distribution +# SPLIT_PROVIDED: Use predefined section splits from geometry +# UNCHANGED: Preserve original geometry discretization +# +# INITIAL CIRCULATION DISTRIBUTIONS: +# ELLIPTIC: Elliptical distribution (optimal for efficiency) +# ZEROS: Start with zero circulation (cold start) +# +# SOLVER TYPES: +# LOOP: Iterative fixed-point solver +# NEWTON: Newton-Raphson nonlinear solver +# +# USAGE NOTES: +# - n_panels should be divisible by n_groups for proper load balancing +# - Higher n_panels improves accuracy but increases computation time +# - Lower relaxation_factor if convergence issues occur +# +# ============================================================================= +# ============================================================================= +# FLIGHT CONDITIONS +# ============================================================================= +# Define the flight state for the aerodynamic analysis +condition: + wind_speed: 10.0 # [m/s] Free stream velocity magnitude + alpha: 5.0 # [°] Angle of attack (pitch angle relative to flow) + beta: 0.0 # [°] Sideslip angle (yaw angle relative to flow) + yaw_rate: 0.0 # [°/s] Yaw rate (for dynamic analysis, 0 for static) + +# ============================================================================= +# WING CONFIGURATION +# ============================================================================= +# Define wing geometry files and discretization parameters wings: - - name: main_wing - n_panels: 40 - n_groups: 40 - spanwise_panel_distribution: LINEAR - spanwise_direction: [0.0, 1.0, 0.0] - remove_nan: true + - name: V3_Kite # Wing identifier for output labeling + yaml_path: data/TUDELFT_V3_KITE/wing_geometry_CAD_CFD_polars_pchip_fitted.yaml + n_panels: 36 # Total number of panels along wingspan + n_groups: 1 # Number of panel groups (must divide n_panels) + spanwise_panel_distribution: LINEAR # Panel spacing algorithm + spanwise_direction: [0.0, 1.0, 0.0] # Unit vector defining wingspan direction + remove_nan: true # Remove NaN values from polar data + +# ============================================================================= +# SOLVER CONFIGURATION +# ============================================================================= +# Numerical method settings and convergence criteria solver_settings: - n_panels: 40 - n_groups: 40 - aerodynamic_model_type: VSM - density: 1.225 # air density [kg/m³] - max_iterations: 1500 - rtol: 1e-5 # relative error [-] - tol_reference_error: 0.001 - relaxation_factor: 0.03 # relaxation factor for convergence - artificial_damping: false # whether to apply artificial damping - k2: 0.1 # artificial damping parameter - k4: 0.0 # artificial damping parameter - type_initial_gamma_distribution: ELLIPTIC - core_radius_fraction: 1e-20 - mu: 1.81e-5 # dynamic viscosity [N·s/m²] - calc_only_f_and_gamma: false # whether to only output f and gamma + # --- Core Aerodynamic Model --- + aerodynamic_model_type: VSM # VSM=3D vortex method, LLT=lifting line theory + solver_type: LOOP # LOOP=fixed-point iteration, NEWTON=Newton-Raphson + + # --- Physical Properties --- + density: 1.225 # [kg/m³] Air density (ISA sea level) + mu: 1.81e-5 # [N·s/m²] Dynamic viscosity (ISA sea level) + + # --- Convergence Control --- + max_iterations: 5000 # Maximum solver iterations before timeout + rtol: 1e-6 # Relative tolerance for convergence + tol_reference_error: 0.001 # Reference error tolerance + relaxation_factor: 0.01 # [0.001-0.1] Under-relaxation for stability + + # --- Numerical Stability --- + artificial_damping: false # Enable artificial damping for unstable cases + k2: 0.1 # 2nd-order damping coefficient + k4: 0.0 # 4th-order damping coefficient + core_radius_fraction: 1e-20 # Vortex core radius (fraction of chord) + + # --- Initial Conditions --- + type_initial_gamma_distribution: ELLIPTIC # Starting circulation distribution + + # --- Output Control --- + calc_only_f_and_gamma: false # true=compute only forces & circulation diff --git a/data/TUDELFT_V3_KITE/geometry_CAD_CFD_polars_pchip_fitted.yaml b/data/TUDELFT_V3_KITE/wing_geometry_CAD_CFD_polars_pchip_fitted.yaml similarity index 100% rename from data/TUDELFT_V3_KITE/geometry_CAD_CFD_polars_pchip_fitted.yaml rename to data/TUDELFT_V3_KITE/wing_geometry_CAD_CFD_polars_pchip_fitted.yaml diff --git a/examples/V3_kite.jl b/examples/V3_kite.jl index 146ad266..f0c3f63d 100644 --- a/examples/V3_kite.jl +++ b/examples/V3_kite.jl @@ -2,14 +2,23 @@ using LinearAlgebra using VortexStepMethod using ControlPlots -# --- User-specified parameters --- -wind_speed = 3.05 # [m/s] -angle_of_attack_deg = 5.0 # [deg] -sideslip_deg = 0.0 -yaw_rate = 0.0 # [rad/s] (not used in static analysis) - project_dir = dirname(dirname(pathof(VortexStepMethod))) # Go up one level from src to project root -yaml_geometry_path = joinpath(project_dir, "data", "TUDELFT_V3_KITE", "geometry_CAD_CFD_polars_pchip_fitted.yaml") + +# Load VSM settings from YAML configuration file +settings = vs("TUDELFT_V3_KITE/vsm_settings.yaml") + +# Extract flight conditions from settings +wind_speed = settings.condition.wind_speed +angle_of_attack_deg = settings.condition.alpha +sideslip_deg = settings.condition.beta +yaw_rate = settings.condition.yaw_rate + +# Use wing geometry path from settings if provided, otherwise use default +yaml_geometry_path = if !isempty(settings.wings[1].yaml_path) + joinpath(project_dir, settings.wings[1].yaml_path) +else + joinpath(project_dir, "data", "TUDELFT_V3_KITE", "wing_geometry_CAD_CFD_polars_pchip_fitted.yaml") +end literature_paths = [ joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv"), joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv"), @@ -19,23 +28,28 @@ literature_paths = [ labels= [ "Julia VSM 2D CFD PCHIP", "CFD RANS Re=5e5", - "CFD RANS Re=10e5", + "CFD RANS Re=10e5 (With Struts)", "Python VSM 2D CFD PCHIP Re=5e5", - "Wind Tunnel Re=5e5" + "Wind Tunnel Re=5e5 (With Struts)" ] -# Create wing, body_aero, and solver objects -wing = YamlWing(yaml_geometry_path; n_panels=36, spanwise_distribution=LINEAR) +# Load VSM settings from YAML configuration file +settings = vs("TUDELFT_V3_KITE/vsm_settings.yaml") + +# Create wing, body_aero, and solver objects using settings +wing = YamlWing(yaml_geometry_path; + n_panels=settings.wings[1].n_panels, + n_groups=settings.wings[1].n_groups, + spanwise_distribution=settings.wings[1].spanwise_panel_distribution +) body_aero = BodyAerodynamics([wing]) solver = Solver(body_aero; - aerodynamic_model_type=VSM, - is_with_artificial_damping=false, - solver_type=LOOP, - density=1.225, - max_iterations=5000, - rtol = 1e-6, - relaxation_factor=0.01, - core_radius_fraction=1e-20, + aerodynamic_model_type=settings.solver_settings.aerodynamic_model_type, + density=settings.solver_settings.density, + max_iterations=settings.solver_settings.max_iterations, + rtol=settings.solver_settings.rtol, + relaxation_factor=settings.solver_settings.relaxation_factor, + core_radius_fraction=settings.solver_settings.core_radius_fraction, ) # Using plotting modules, to create more comprehensive plots @@ -48,12 +62,12 @@ PLOT && plot_polars( [body_aero], labels, literature_path_list=literature_paths, - angle_range=range(1, 20, length=20), + angle_range=range(-5, 25, length=30), angle_type="angle_of_attack", angle_of_attack=angle_of_attack_deg, side_slip=sideslip_deg, v_a=wind_speed, - title="$(wing.n_panels)_distribution_$(wing.spanwise_distribution)", + title="$(wing.n_panels)_panels_$(wing.spanwise_distribution)_from_yaml_settings", data_type=".pdf", is_save=false, is_show=true, diff --git a/src/settings.jl b/src/settings.jl index 65594076..9efd4498 100644 --- a/src/settings.jl +++ b/src/settings.jl @@ -1,5 +1,13 @@ +@with_kw mutable struct ConditionSettings + wind_speed::Float64 = 10.0 # wind speed [m/s] + alpha::Float64 = 5.0 # angle of attack [°] + beta::Float64 = 0.0 # sideslip angle [°] + yaw_rate::Float64 = 0.0 # yaw rate [°/s] +end + @with_kw mutable struct WingSettings name::String = "main_wing" + yaml_path::String = "" # path to wing geometry YAML file n_panels::Int64 = 40 n_groups::Int64 = 40 spanwise_panel_distribution::PanelDistribution = LINEAR @@ -11,6 +19,7 @@ end n_panels::Int64 = 40 n_groups::Int64 = 40 aerodynamic_model_type::Model = VSM + solver_type::String = "LOOP" # type of solver density::Float64 = 1.225 # air density [kg/m³] max_iterations::Int64 = 1500 rtol::Float64 = 1e-5 # relative error [-] @@ -26,6 +35,7 @@ end end @Base.kwdef mutable struct VSMSettings + condition::ConditionSettings = ConditionSettings() wings::Vector{WingSettings} = [] solver_settings::SolverSettings = SolverSettings() end @@ -35,10 +45,23 @@ function vs(filename) data = YAML.load_file(joinpath("data", filename)) n_panels = 0 n_groups = 0 + + # Load condition settings if present + if haskey(data, "condition") + condition = data["condition"] + res.condition.wind_speed = condition["wind_speed"] + res.condition.alpha = condition["alpha"] + res.condition.beta = condition["beta"] + res.condition.yaw_rate = condition["yaw_rate"] + end + # add and update wing settings for (i, wing) in pairs(data["wings"]) push!(res.wings, WingSettings()) res.wings[i].name = wing["name"] + if haskey(wing, "yaml_path") + res.wings[i].yaml_path = wing["yaml_path"] + end res.wings[i].n_panels = wing["n_panels"] n_panels += res.wings[i].n_panels res.wings[i].n_groups = wing["n_groups"] @@ -52,6 +75,9 @@ function vs(filename) res.solver_settings.n_panels = n_panels res.solver_settings.n_groups = n_groups res.solver_settings.aerodynamic_model_type = eval(Symbol(solver["aerodynamic_model_type"])) + if haskey(solver, "solver_type") + res.solver_settings.solver_type = solver["solver_type"] + end res.solver_settings.density = solver["density"] res.solver_settings.max_iterations = solver["max_iterations"] res.solver_settings.rtol = solver["rtol"] @@ -69,6 +95,7 @@ end function Base.show(io::IO, vs::VSMSettings) println(io, "VSMSettings:") + print(io, replace(repr(vs.condition), "\n" => "\n ")) for (i, wing) in pairs(vs.wings) if i==1 print(io, " ") From dd659cad08c173f5aaa6833b6020ff2540557213 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Tue, 5 Aug 2025 11:46:21 +0200 Subject: [PATCH 11/26] #155 adjusted V3_kite, to be specified from a .yaml --- examples/V3_kite.jl | 31 ++++++++++++++----------------- 1 file changed, 14 insertions(+), 17 deletions(-) diff --git a/examples/V3_kite.jl b/examples/V3_kite.jl index f0c3f63d..c397aff1 100644 --- a/examples/V3_kite.jl +++ b/examples/V3_kite.jl @@ -13,12 +13,6 @@ angle_of_attack_deg = settings.condition.alpha sideslip_deg = settings.condition.beta yaw_rate = settings.condition.yaw_rate -# Use wing geometry path from settings if provided, otherwise use default -yaml_geometry_path = if !isempty(settings.wings[1].yaml_path) - joinpath(project_dir, settings.wings[1].yaml_path) -else - joinpath(project_dir, "data", "TUDELFT_V3_KITE", "wing_geometry_CAD_CFD_polars_pchip_fitted.yaml") -end literature_paths = [ joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv"), joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv"), @@ -37,7 +31,7 @@ labels= [ settings = vs("TUDELFT_V3_KITE/vsm_settings.yaml") # Create wing, body_aero, and solver objects using settings -wing = YamlWing(yaml_geometry_path; +wing = YamlWing(settings.wings[1].yaml_path; n_panels=settings.wings[1].n_panels, n_groups=settings.wings[1].n_groups, spanwise_distribution=settings.wings[1].spanwise_panel_distribution @@ -51,6 +45,19 @@ solver = Solver(body_aero; relaxation_factor=settings.solver_settings.relaxation_factor, core_radius_fraction=settings.solver_settings.core_radius_fraction, ) +# Set flight conditions +α = deg2rad(settings.condition.alpha) +β = deg2rad(settings.condition.beta) +va = settings.condition.wind_speed * [ + cos(α)*cos(β), # X_b (forward) + sin(β), # Y_b (right) + sin(α)*cos(β) # Z_b (down) +] +set_va!(body_aero, va) +# Run the solver +results = VortexStepMethod.solve(solver, body_aero; log=true) + + # Using plotting modules, to create more comprehensive plots PLOT = true @@ -76,16 +83,6 @@ PLOT && plot_polars( # Plotting geometry -#--- Set apparent wind vector in body axes --- -α = deg2rad(angle_of_attack_deg) -β = deg2rad(sideslip_deg) -va = wind_speed * [ - cos(α)*cos(β), # X_b (forward) - sin(β), # Y_b (right) - sin(α)*cos(β) # Z_b (down) -] -set_va!(body_aero, va) - results = VortexStepMethod.solve(solver, body_aero; log=true) PLOT && plot_geometry( body_aero, From 8942409a8e9ce5322b1cf8fbf3a8876d2751fa74 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Tue, 5 Aug 2025 13:08:30 +0200 Subject: [PATCH 12/26] #155 working, with Wing constructor --- data/TUDELFT_V3_KITE/vsm_settings.yaml | 25 ++---- examples/V3_kite.jl | 2 +- src/body_aerodynamics.jl | 18 ++--- src/precompile.jl | 22 ++---- src/settings.jl | 6 +- src/solver.jl | 16 ++-- src/yaml_geometry.jl | 104 +++++-------------------- 7 files changed, 55 insertions(+), 138 deletions(-) diff --git a/data/TUDELFT_V3_KITE/vsm_settings.yaml b/data/TUDELFT_V3_KITE/vsm_settings.yaml index 09eb41fa..6ee01847 100644 --- a/data/TUDELFT_V3_KITE/vsm_settings.yaml +++ b/data/TUDELFT_V3_KITE/vsm_settings.yaml @@ -33,12 +33,7 @@ # - n_panels should be divisible by n_groups for proper load balancing # - Higher n_panels improves accuracy but increases computation time # - Lower relaxation_factor if convergence issues occur -# -# ============================================================================= -# ============================================================================= -# FLIGHT CONDITIONS -# ============================================================================= # Define the flight state for the aerodynamic analysis condition: wind_speed: 10.0 # [m/s] Free stream velocity magnitude @@ -46,22 +41,16 @@ condition: beta: 0.0 # [°] Sideslip angle (yaw angle relative to flow) yaw_rate: 0.0 # [°/s] Yaw rate (for dynamic analysis, 0 for static) -# ============================================================================= -# WING CONFIGURATION -# ============================================================================= # Define wing geometry files and discretization parameters wings: - - name: V3_Kite # Wing identifier for output labeling - yaml_path: data/TUDELFT_V3_KITE/wing_geometry_CAD_CFD_polars_pchip_fitted.yaml - n_panels: 36 # Total number of panels along wingspan - n_groups: 1 # Number of panel groups (must divide n_panels) - spanwise_panel_distribution: LINEAR # Panel spacing algorithm - spanwise_direction: [0.0, 1.0, 0.0] # Unit vector defining wingspan direction - remove_nan: true # Remove NaN values from polar data + - name: V3_Kite # Wing identifier for output labeling + geometry_file: data/TUDELFT_V3_KITE/wing_geometry_CAD_CFD_polars_pchip_fitted.yaml + n_panels: 36 # Total number of panels along wingspan + n_groups: 1 # Number of panel groups (must divide n_panels) + spanwise_panel_distribution: LINEAR # Panel spacing algorithm + spanwise_direction: [0.0, 1.0, 0.0] # Unit vector defining wingspan direction + remove_nan: true # Remove NaN values from polar data -# ============================================================================= -# SOLVER CONFIGURATION -# ============================================================================= # Numerical method settings and convergence criteria solver_settings: # --- Core Aerodynamic Model --- diff --git a/examples/V3_kite.jl b/examples/V3_kite.jl index c397aff1..85154a95 100644 --- a/examples/V3_kite.jl +++ b/examples/V3_kite.jl @@ -31,7 +31,7 @@ labels= [ settings = vs("TUDELFT_V3_KITE/vsm_settings.yaml") # Create wing, body_aero, and solver objects using settings -wing = YamlWing(settings.wings[1].yaml_path; +wing = YamlWing(settings.wings[1].geometry_file; n_panels=settings.wings[1].n_panels, n_groups=settings.wings[1].n_groups, spanwise_distribution=settings.wings[1].spanwise_panel_distribution diff --git a/src/body_aerodynamics.jl b/src/body_aerodynamics.jl index 50a34fe3..ef0509c8 100644 --- a/src/body_aerodynamics.jl +++ b/src/body_aerodynamics.jl @@ -18,24 +18,24 @@ Main structure for calculating aerodynamic properties of bodies. Use the constru - `work_vectors`::NTuple{10, MVec3} = ntuple(_ -> zeros(MVec3), 10) - `AIC::Array{Float64, 3}` = zeros(3, P, P) - `projected_area::Float64` = 1.0: The area projected onto the xy-plane of the kite body reference frame [m²] -- `y::MVector{P, Float64}` = zeros(MVector{P, Float64}) +- `y::MVector{P, Float64}` = MVector{P,Float64}(zeros(P)) - `cache::Vector{PreallocationTools.LazyBufferCache{typeof(identity), typeof(identity)}}` = [LazyBufferCache() for _ in 1:5] """ @with_kw mutable struct BodyAerodynamics{P} panels::Vector{Panel} - wings::Union{Vector{Wing}, Vector{RamAirWing}, Vector{YamlWing}} + wings::Union{Vector{Wing}, Vector{RamAirWing}} _va::MVec3 = zeros(MVec3) omega::MVec3 = zeros(MVec3) - gamma_distribution::MVector{P, Float64} = zeros(MVector{P, Float64}) - alpha_uncorrected::MVector{P, Float64} = zeros(MVector{P, Float64}) - alpha_corrected::MVector{P, Float64} = zeros(MVector{P, Float64}) - stall_angle_list::MVector{P, Float64} = zeros(MVector{P, Float64}) - alpha_array::MVector{P, Float64} = zeros(MVector{P, Float64}) - v_a_array::MVector{P, Float64} = zeros(MVector{P, Float64}) + gamma_distribution::MVector{P, Float64} = zeros(P) + alpha_uncorrected::MVector{P, Float64} = zeros(P) + alpha_corrected::MVector{P, Float64} = zeros(P) + stall_angle_list::MVector{P, Float64} = zeros(P) + alpha_array::MVector{P, Float64} = zeros(P) + v_a_array::MVector{P, Float64} = zeros(P) work_vectors::NTuple{10,MVec3} = ntuple(_ -> zeros(MVec3), 10) AIC::Array{Float64, 3} = zeros(3, P, P) projected_area::Float64 = one(Float64) - y::MVector{P, Float64} = zeros(MVector{P, Float64}) + y::MVector{P, Float64} = zeros(P) cache::Vector{PreallocationTools.LazyBufferCache{typeof(identity), typeof(identity)}} = [LazyBufferCache() for _ in 1:5] end diff --git a/src/precompile.jl b/src/precompile.jl index c6f13e39..cd9a44ab 100644 --- a/src/precompile.jl +++ b/src/precompile.jl @@ -1,21 +1,16 @@ @setup_workload begin # Putting some things in `@setup_workload` instead of `@compile_workload` can reduce the size of the # precompile file and potentially make loading faster. - # list = [OtherType("hello"), OtherType("world!")] - path = dirname(pathof(@__MODULE__)) - + @compile_workload begin + # Minimal precompilation to avoid segfault # all calls in this block will be precompiled, regardless of whether # they belong to your package or not (on Julia 1.8 and higher) - vss = vs(joinpath(path, "../data/vsm_settings_dual.yaml")) + # Step 1: Define wing parameters - n_panels = 20 # Number of panels - span = 20.0 # Wing span [m] + n_panels = 2 # Reduced number of panels for faster precompilation + span = 10.0 # Wing span [m] chord = 1.0 # Chord length [m] - v_a = 20.0 # Magnitude of inflow velocity [m/s] - density = 1.225 # Air density [kg/m³] - alpha_deg = 30.0 # Angle of attack [degrees] - alpha = deg2rad(alpha_deg) # Step 2: Create wing geometry with linear panel distribution wing = Wing(n_panels, spanwise_distribution=LINEAR) @@ -30,11 +25,8 @@ [chord, -span/2, 0.0], # Right tip TE INVISCID) - # Step 3: Initialize aerodynamics - body_aero::BodyAerodynamics = BodyAerodynamics([wing]) - - gamma_initial = zeros(length(body_aero.panels)) - calculate_circulation_distribution_elliptical_wing(gamma_initial, body_aero) + # Step 3: Initialize aerodynamics (simplified) + body_aero = BodyAerodynamics([wing]) nothing end diff --git a/src/settings.jl b/src/settings.jl index 9efd4498..0e9d7d2e 100644 --- a/src/settings.jl +++ b/src/settings.jl @@ -7,7 +7,7 @@ end @with_kw mutable struct WingSettings name::String = "main_wing" - yaml_path::String = "" # path to wing geometry YAML file + geometry_file::String = "" # path to wing geometry YAML file n_panels::Int64 = 40 n_groups::Int64 = 40 spanwise_panel_distribution::PanelDistribution = LINEAR @@ -59,8 +59,8 @@ function vs(filename) for (i, wing) in pairs(data["wings"]) push!(res.wings, WingSettings()) res.wings[i].name = wing["name"] - if haskey(wing, "yaml_path") - res.wings[i].yaml_path = wing["yaml_path"] + if haskey(wing, "geometry_file") + res.wings[i].geometry_file = wing["geometry_file"] end res.wings[i].n_panels = wing["n_panels"] n_panels += res.wings[i].n_panels diff --git a/src/solver.jl b/src/solver.jl index 36a8b632..3247e669 100644 --- a/src/solver.jl +++ b/src/solver.jl @@ -47,23 +47,23 @@ Struct for storing the solution of the [solve!](@ref) function. Must contain all moment::MVec3 = zeros(MVec3) force_coeffs::MVec3 = zeros(MVec3) moment_coeffs::MVec3 = zeros(MVec3) - moment_dist::MVector{P, Float64} = zeros(MVector{P, Float64}) - moment_coeff_dist::MVector{P, Float64} = zeros(MVector{P, Float64}) - group_moment_dist::MVector{G, Float64} = zeros(MVector{G, Float64}) - group_moment_coeff_dist::MVector{G, Float64} = zeros(MVector{G, Float64}) + moment_dist::MVector{P, Float64} = zeros(P) + moment_coeff_dist::MVector{P, Float64} = zeros(P) + group_moment_dist::MVector{G, Float64} = zeros(G) + group_moment_coeff_dist::MVector{G, Float64} = zeros(G) solver_status::SolverStatus = FAILURE end # Output of the function gamma_loop! @with_kw mutable struct LoopResult{P} converged::Bool = false - gamma_new::MVector{P, Float64} = zeros(MVector{P, Float64}) - alpha_array::MVector{P, Float64} = zeros(MVector{P, Float64}) # TODO: Is this different from BodyAerodynamics.alpha_array ? - v_a_array::MVector{P, Float64} = zeros(MVector{P, Float64}) + gamma_new::MVector{P, Float64} = zeros(P) + alpha_array::MVector{P, Float64} = zeros(P) # TODO: Is this different from BodyAerodynamics.alpha_array ? + v_a_array::MVector{P, Float64} = zeros(P) end @with_kw struct BaseResult{P} - va_norm_array::MVector{P, Float64} = zeros(MVector{P, Float64}) + va_norm_array::MVector{P, Float64} = zeros(P) va_unit_array::Matrix{Float64} = zeros(P, 3) end diff --git a/src/yaml_geometry.jl b/src/yaml_geometry.jl index d8242a38..0136b7f1 100644 --- a/src/yaml_geometry.jl +++ b/src/yaml_geometry.jl @@ -1,67 +1,4 @@ -""" - @with_kw mutable struct AirfoilSettings - -Configuration settings for airfoils loaded from YAML files. - -This struct stores the mapping between airfoil IDs and their aerodynamic data sources, -typically CSV files containing polar data. It preserves the original YAML configuration -for reference and enables reconstruction of the wing geometry from YAML specifications. - -# Fields -- `airfoil_id::Int64`: Unique identifier for the airfoil section -- `type::String`: Type of aerodynamic data (e.g., "polars", "inviscid") -- `info_dict::Dict{String, Any}`: Additional configuration data, typically containing - file paths to CSV polar data files and other airfoil-specific parameters - -# Example -```julia -# Typical usage when parsing YAML wing configuration -settings = AirfoilSettings( - airfoil_id = 1, - type = "polars", - info_dict = Dict("csv_file_path" => "polars/airfoil_1.csv") -) -``` -""" -@with_kw mutable struct AirfoilSettings - airfoil_id::Int64 - type::String - info_dict::Dict{String, Any} -end -""" - YamlWing <: AbstractWing - -A wing model created from YAML configuration files with CSV polar data. - -## Core Features -- Wing geometry defined through YAML section coordinates -- Aerodynamic properties based on CSV polar data files -- Support for multiple airfoil types per wing -- Configurable panel distribution and geometry parameters - -## Notable Fields -- `n_panels::Int16`: Number of panels in aerodynamic mesh -- `n_groups::Int16`: Number of control groups -- `spanwise_distribution::PanelDistribution`: Panel distribution type -- `sections::Vector{Section}`: Wing cross-sections with aerodynamic data -- `airfoil_settings::Vector{AirfoilSettings}`: Airfoil configuration data - -See constructor `YamlWing(yaml_path; kwargs...)` for usage details. -""" -mutable struct YamlWing <: AbstractWing - n_panels::Int16 - n_groups::Int16 - spanwise_distribution::PanelDistribution - panel_props::PanelProperties - spanwise_direction::MVec3 - sections::Vector{Section} - refined_sections::Vector{Section} - remove_nan::Bool - - # Essential YAML-specific fields - airfoil_settings::Vector{AirfoilSettings} -end """ load_polar_data(csv_file_path) @@ -124,7 +61,7 @@ end """ - YamlWing(yaml_path; kwargs...) + YamlWing(geometry_file; kwargs...) Create a wing model from YAML configuration file with CSV polar data. @@ -135,7 +72,7 @@ This constructor builds a complete aerodynamic model by: 4. Setting up panel distribution and geometric properties # Arguments -- `yaml_path`: Path to YAML file containing wing geometry and airfoil specifications +- `geometry_file`: Path to YAML file containing wing geometry and airfoil specifications # Keyword Arguments - `n_panels=20`: Number of aerodynamic panels across wingspan @@ -146,7 +83,7 @@ This constructor builds a complete aerodynamic model by: - `prn=true`: Print info messages during construction # Returns -A fully initialized `YamlWing` instance ready for aerodynamic simulation. +A fully initialized `Wing` instance ready for aerodynamic simulation. # Example YAML format ```yaml @@ -176,7 +113,7 @@ wing = YamlWing( ``` """ function YamlWing( - yaml_path; + geometry_file; n_panels=20, n_groups=1, spanwise_distribution=LINEAR, @@ -187,27 +124,30 @@ function YamlWing( !(n_panels % n_groups == 0) && throw(ArgumentError("Number of panels should be divisible by number of groups")) !isapprox(spanwise_direction, [0.0, 1.0, 0.0]) && throw(ArgumentError("Spanwise direction has to be [0.0, 1.0, 0.0], not $spanwise_direction")) - prn && @info "Reading YAML wing configuration from $yaml_path" + prn && @info "Reading YAML wing configuration from $geometry_file" # Read and parse YAML file - yaml_data = YAML.load_file(yaml_path) + yaml_data = YAML.load_file(geometry_file) # Parse airfoils and create CSV file mapping airfoil_csv_map = Dict{Int64, String}() - airfoil_settings = AirfoilSettings[] for row in yaml_data["wing_airfoils"]["data"] airfoil_dict = Dict(zip(yaml_data["wing_airfoils"]["headers"], row)) airfoil_id, airfoil_type, info_dict = airfoil_dict["airfoil_id"], airfoil_dict["type"], airfoil_dict["info_dict"] - push!(airfoil_settings, AirfoilSettings(airfoil_id, airfoil_type, info_dict)) haskey(info_dict, "csv_file_path") && (airfoil_csv_map[airfoil_id] = info_dict["csv_file_path"]) end - # Parse sections and create wing sections - sections = Section[] - refined_sections = Section[] + # Create Wing using the standard constructor + wing = Wing(n_panels; + n_groups=n_groups, + spanwise_distribution=spanwise_distribution, + spanwise_direction=MVec3(spanwise_direction), + remove_nan=remove_nan + ) + # Parse sections and populate wing for row in yaml_data["wing_sections"]["data"] section_dict = Dict(zip(yaml_data["wing_sections"]["headers"], row)) airfoil_id = section_dict["airfoil_id"] @@ -220,21 +160,17 @@ function YamlWing( csv_file_path = get(airfoil_csv_map, airfoil_id, "") if !isempty(csv_file_path) && !isabspath(csv_file_path) # Make relative paths relative to YAML file directory - csv_file_path = joinpath(dirname(yaml_path), csv_file_path) + csv_file_path = joinpath(dirname(geometry_file), csv_file_path) end aero_data, aero_model = load_polar_data(csv_file_path) prn && println("Section airfoil_id $airfoil_id: Using $aero_model model") - section = Section(le_coord, te_coord, aero_model, aero_data) - push!(sections, section) - push!(refined_sections, Section(le_coord, te_coord, aero_model, aero_data)) + add_section!(wing, le_coord, te_coord, aero_model, aero_data) end - # Create YamlWing - YamlWing( - n_panels, n_groups, spanwise_distribution, PanelProperties{n_panels}(), - MVec3(spanwise_direction), sections, refined_sections, remove_nan, - airfoil_settings - ) + # Initialize the wing after adding all sections + reinit!(wing) + + return wing end From af11c408e2b1095586bdf77a6ca8da8c34e31f68 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Tue, 5 Aug 2025 13:21:20 +0200 Subject: [PATCH 13/26] #155 #185 added StructMapping for yaml parsing --- Project.toml | 4 +- src/VortexStepMethod.jl | 6 +-- src/settings.jl | 91 ++++++++++++++++++++----------------- src/yaml_geometry.jl | 99 +++++++++++++++++++++++++++++++++-------- 4 files changed, 136 insertions(+), 64 deletions(-) diff --git a/Project.toml b/Project.toml index 7487a232..c7e7cd2e 100644 --- a/Project.toml +++ b/Project.toml @@ -23,6 +23,7 @@ SciMLBase = "0bca4576-84f4-4d90-8ffe-ffa030f20462" Serialization = "9e88b42a-f829-5b0c-bbe9-9e923198166b" StaticArrays = "90137ffa-7385-5640-81b9-e52037218182" Statistics = "10745b16-79ce-11e8-11f9-7d13ad32a3b2" +StructMapping = "7c3b921d-20d6-4eba-ad57-605525e86ab2" Timers = "21f18d07-b854-4dab-86f0-c15a3821819a" Xfoil = "19641d66-a62d-11e8-2441-8f57a969a9c4" YAML = "ddb6d928-2868-570f-bddf-ab3f9cf99eb6" @@ -59,6 +60,7 @@ SciMLBase = "2.77.0" Serialization = "1" StaticArrays = "1" Statistics = "1" +StructMapping = "0.2.3" Test = "1" Timers = "0.1" Xfoil = "0.5" @@ -75,4 +77,4 @@ Documenter = "e30172f5-a6a5-5a46-863b-614d45cd2de4" Test = "8dfed614-e22c-5e08-85e1-65c5234f0b40" [targets] -test = ["Test", "DataFrames", "CSV", "Documenter", "BenchmarkTools", "ControlPlots", "Aqua"] \ No newline at end of file +test = ["Test", "DataFrames", "CSV", "Documenter", "BenchmarkTools", "ControlPlots", "Aqua"] diff --git a/src/VortexStepMethod.jl b/src/VortexStepMethod.jl index bedae5f5..ffb7ae6c 100644 --- a/src/VortexStepMethod.jl +++ b/src/VortexStepMethod.jl @@ -12,7 +12,7 @@ using LaTeXStrings using NonlinearSolve import NonlinearSolve: solve!, solve using Interpolations -using Interpolations: Extrapolation +import Interpolations: Extrapolation using Parameters using Serialization using Timers @@ -22,6 +22,7 @@ using Pkg using DifferentiationInterface import SciMLBase: successful_retcode import YAML +using StructMapping using Xfoil # Export public interface @@ -40,13 +41,12 @@ export InitialGammaDistribution, ELLIPTIC, ZEROS export SolverStatus, FEASIBLE, INFEASIBLE, FAILURE export SolverType, LOOP, NONLIN -export plot_geometry, plot_distribution, plot_circulation_distribution, plot_geometry, plot_polars, save_plot, show_plot, plot_polar_data +export plot_geometry, plot_distribution, plot_circulation_distribution, plot_polars, save_plot, show_plot, plot_polar_data # the following functions are defined in ext/VortexStepMethodExt.jl function plot_geometry end function plot_distribution end function plot_circulation_distribution end -function plot_geometry end function plot_polars end function save_plot end function show_plot end diff --git a/src/settings.jl b/src/settings.jl index 0e9d7d2e..56e6694b 100644 --- a/src/settings.jl +++ b/src/settings.jl @@ -41,56 +41,63 @@ end end function vs(filename) - res = VSMSettings() + # Uwe's suggested 3-line approach using StructMapping.jl (adapted) data = YAML.load_file(joinpath("data", filename)) - n_panels = 0 - n_groups = 0 - # Load condition settings if present + # Use StructMapping for basic structure conversion + # But handle special fields manually due to enum conversion needs + vsm_settings = VSMSettings() + + # Convert condition settings using StructMapping if haskey(data, "condition") - condition = data["condition"] - res.condition.wind_speed = condition["wind_speed"] - res.condition.alpha = condition["alpha"] - res.condition.beta = condition["beta"] - res.condition.yaw_rate = condition["yaw_rate"] + vsm_settings.condition = convertdict(ConditionSettings, data["condition"]) end - # add and update wing settings - for (i, wing) in pairs(data["wings"]) - push!(res.wings, WingSettings()) - res.wings[i].name = wing["name"] - if haskey(wing, "geometry_file") - res.wings[i].geometry_file = wing["geometry_file"] + # Convert wing settings manually due to enum conversions + n_panels = 0 + n_groups = 0 + + if haskey(data, "wings") + for wing_data in data["wings"] + wing = WingSettings() + wing.name = wing_data["name"] + if haskey(wing_data, "geometry_file") + wing.geometry_file = wing_data["geometry_file"] + end + wing.n_panels = wing_data["n_panels"] + wing.n_groups = wing_data["n_groups"] + wing.spanwise_panel_distribution = eval(Symbol(wing_data["spanwise_panel_distribution"])) + wing.spanwise_direction = MVec3(wing_data["spanwise_direction"]) + wing.remove_nan = wing_data["remove_nan"] + + push!(vsm_settings.wings, wing) + n_panels += wing.n_panels + n_groups += wing.n_groups end - res.wings[i].n_panels = wing["n_panels"] - n_panels += res.wings[i].n_panels - res.wings[i].n_groups = wing["n_groups"] - n_groups += res.wings[i].n_groups - res.wings[i].spanwise_panel_distribution = eval(Symbol(wing["spanwise_panel_distribution"])) - res.wings[i].spanwise_direction = MVec3(wing["spanwise_direction"]) - res.wings[i].remove_nan = wing["remove_nan"] end - # update solver settings - solver = data["solver_settings"] - res.solver_settings.n_panels = n_panels - res.solver_settings.n_groups = n_groups - res.solver_settings.aerodynamic_model_type = eval(Symbol(solver["aerodynamic_model_type"])) - if haskey(solver, "solver_type") - res.solver_settings.solver_type = solver["solver_type"] + + # Convert solver settings using StructMapping base, then override special fields + if haskey(data, "solver_settings") + solver_data = data["solver_settings"] + + # Create a copy of solver_data with string fields for enums removed + solver_data_clean = copy(solver_data) + delete!(solver_data_clean, "aerodynamic_model_type") + delete!(solver_data_clean, "type_initial_gamma_distribution") + + # Use StructMapping for the basic fields + vsm_settings.solver_settings = convertdict(SolverSettings, solver_data_clean) + + # Handle enum conversions manually + vsm_settings.solver_settings.aerodynamic_model_type = eval(Symbol(solver_data["aerodynamic_model_type"])) + vsm_settings.solver_settings.type_initial_gamma_distribution = eval(Symbol(solver_data["type_initial_gamma_distribution"])) + + # Override with calculated totals + vsm_settings.solver_settings.n_panels = n_panels + vsm_settings.solver_settings.n_groups = n_groups end - res.solver_settings.density = solver["density"] - res.solver_settings.max_iterations = solver["max_iterations"] - res.solver_settings.rtol = solver["rtol"] - res.solver_settings.tol_reference_error = solver["tol_reference_error"] - res.solver_settings.relaxation_factor = solver["relaxation_factor"] - res.solver_settings.artificial_damping = solver["artificial_damping"] - res.solver_settings.k2 = solver["k2"] - res.solver_settings.k4 = solver["k4"] - res.solver_settings.type_initial_gamma_distribution = eval(Symbol(solver["type_initial_gamma_distribution"])) - res.solver_settings.core_radius_fraction = solver["core_radius_fraction"] - res.solver_settings.mu = solver["mu"] - res.solver_settings.calc_only_f_and_gamma = solver["calc_only_f_and_gamma"] - res + + return vsm_settings end function Base.show(io::IO, vs::VSMSettings) diff --git a/src/yaml_geometry.jl b/src/yaml_geometry.jl index 0136b7f1..c6d77494 100644 --- a/src/yaml_geometry.jl +++ b/src/yaml_geometry.jl @@ -12,6 +12,45 @@ Expected format: header row and columns alpha, cl, cd, cm (case-insensitive, ord Returns (aero_data, POLAR_VECTORS) or (nothing, INVISCID) if missing/invalid. """ + +# Structs for YAML parsing using StructMapping.jl +@kwdef struct WingAirfoilInfo + csv_file_path::String = "" +end + +@kwdef struct WingAirfoilData + airfoil_id::Int64 + type::String + info_dict::WingAirfoilInfo +end + +@kwdef struct WingAirfoils + alpha_range::Vector{Float64} + reynolds::Float64 + headers::Vector{String} + data::Vector{WingAirfoilData} +end + +@kwdef struct WingSectionData + airfoil_id::Int64 + LE_x::Float64 + LE_y::Float64 + LE_z::Float64 + TE_x::Float64 + TE_y::Float64 + TE_z::Float64 +end + +@kwdef struct WingSections + headers::Vector{String} + data::Vector{WingSectionData} +end + +@kwdef struct WingGeometry + wing_sections::WingSections + wing_airfoils::WingAirfoils +end + function load_polar_data(csv_file_path::String) if isempty(csv_file_path) || !isfile(csv_file_path) @warn "Polar file not found or empty path: $csv_file_path. Using INVISCID model instead." @@ -126,17 +165,44 @@ function YamlWing( prn && @info "Reading YAML wing configuration from $geometry_file" - # Read and parse YAML file - yaml_data = YAML.load_file(geometry_file) + # Load YAML file following Uwe's suggestion + data = YAML.load_file(geometry_file) - # Parse airfoils and create CSV file mapping - airfoil_csv_map = Dict{Int64, String}() + # Convert YAML data to our struct format + # Convert wing sections + wing_sections_data = data["wing_sections"] + sections = WingSectionData[] + for row in wing_sections_data["data"] + section_dict = Dict(zip(wing_sections_data["headers"], row)) + push!(sections, WingSectionData( + airfoil_id = section_dict["airfoil_id"], + LE_x = section_dict["LE_x"], + LE_y = section_dict["LE_y"], + LE_z = section_dict["LE_z"], + TE_x = section_dict["TE_x"], + TE_y = section_dict["TE_y"], + TE_z = section_dict["TE_z"] + )) + end - for row in yaml_data["wing_airfoils"]["data"] - airfoil_dict = Dict(zip(yaml_data["wing_airfoils"]["headers"], row)) - airfoil_id, airfoil_type, info_dict = airfoil_dict["airfoil_id"], airfoil_dict["type"], airfoil_dict["info_dict"] - - haskey(info_dict, "csv_file_path") && (airfoil_csv_map[airfoil_id] = info_dict["csv_file_path"]) + # Convert wing airfoils + wing_airfoils_data = data["wing_airfoils"] + airfoils = WingAirfoilData[] + for row in wing_airfoils_data["data"] + airfoil_dict = Dict(zip(wing_airfoils_data["headers"], row)) + push!(airfoils, WingAirfoilData( + airfoil_id = airfoil_dict["airfoil_id"], + type = airfoil_dict["type"], + info_dict = WingAirfoilInfo(csv_file_path = get(airfoil_dict["info_dict"], "csv_file_path", "")) + )) + end + + # Create CSV file mapping from airfoils + airfoil_csv_map = Dict{Int64, String}() + for airfoil in airfoils + if !isempty(airfoil.info_dict.csv_file_path) + airfoil_csv_map[airfoil.airfoil_id] = airfoil.info_dict.csv_file_path + end end # Create Wing using the standard constructor @@ -148,23 +214,20 @@ function YamlWing( ) # Parse sections and populate wing - for row in yaml_data["wing_sections"]["data"] - section_dict = Dict(zip(yaml_data["wing_sections"]["headers"], row)) - airfoil_id = section_dict["airfoil_id"] - - # Get coordinates - le_coord = [section_dict["LE_x"], section_dict["LE_y"], section_dict["LE_z"]] - te_coord = [section_dict["TE_x"], section_dict["TE_y"], section_dict["TE_z"]] + for section in sections + # Get coordinates directly from struct fields + le_coord = [section.LE_x, section.LE_y, section.LE_z] + te_coord = [section.TE_x, section.TE_y, section.TE_z] # Load polar data and create section - csv_file_path = get(airfoil_csv_map, airfoil_id, "") + csv_file_path = get(airfoil_csv_map, section.airfoil_id, "") if !isempty(csv_file_path) && !isabspath(csv_file_path) # Make relative paths relative to YAML file directory csv_file_path = joinpath(dirname(geometry_file), csv_file_path) end aero_data, aero_model = load_polar_data(csv_file_path) - prn && println("Section airfoil_id $airfoil_id: Using $aero_model model") + prn && println("Section airfoil_id $(section.airfoil_id): Using $aero_model model") add_section!(wing, le_coord, te_coord, aero_model, aero_data) end From 5e56cc3e99fb2e1999f59af5f65e5f6b8825c01b Mon Sep 17 00:00:00 2001 From: jellepoland Date: Tue, 5 Aug 2025 13:51:13 +0200 Subject: [PATCH 14/26] #185 #155 created ram_air_kite folder, all tests passing --- data/pyramid_model/geometry.yaml | 100 +++++---- data/pyramid_model/polars/1.csv | 88 ++------ data/pyramid_model/polars/2.csv | 71 ------- data/{ => ram_air_kite}/ram_air_kite_body.obj | 0 data/{ => ram_air_kite}/ram_air_kite_foil.dat | 0 .../ram_air_kite_foil_cd_polar.csv | 0 .../ram_air_kite_foil_cl_polar.csv | 0 .../ram_air_kite_foil_cm_polar.csv | 0 data/{ => ram_air_kite}/vsm_settings.yaml | 0 .../{ => ram_air_kite}/vsm_settings_dual.yaml | 0 examples/bench.jl | 2 +- examples/cleanup.jl | 6 +- examples/pyramid_model.jl | 192 +++++++++--------- examples/ram_air_kite.jl | 2 +- src/settings.jl | 2 +- test/test_plotting.jl | 4 +- test/test_results.jl | 16 +- test/test_settings.jl | 4 +- 18 files changed, 195 insertions(+), 292 deletions(-) delete mode 100644 data/pyramid_model/polars/2.csv rename data/{ => ram_air_kite}/ram_air_kite_body.obj (100%) rename data/{ => ram_air_kite}/ram_air_kite_foil.dat (100%) rename data/{ => ram_air_kite}/ram_air_kite_foil_cd_polar.csv (100%) rename data/{ => ram_air_kite}/ram_air_kite_foil_cl_polar.csv (100%) rename data/{ => ram_air_kite}/ram_air_kite_foil_cm_polar.csv (100%) rename data/{ => ram_air_kite}/vsm_settings.yaml (100%) rename data/{ => ram_air_kite}/vsm_settings_dual.yaml (100%) diff --git a/data/pyramid_model/geometry.yaml b/data/pyramid_model/geometry.yaml index a239c433..dfbb71bb 100644 --- a/data/pyramid_model/geometry.yaml +++ b/data/pyramid_model/geometry.yaml @@ -1,52 +1,68 @@ +# Kite system geometry for simulation based on provided Julia code + wing_sections: # --------------------------------------------------------------- - # headers: - # - airfoil_id: integer, unique identifier for the airfoil (matches wing_airfoils) - # - LE_x: x-coordinate of leading edge - # - LE_y: y-coordinate of leading edge - # - LE_z: z-coordinate of leading edge - # - TE_x: x-coordinate of trailing edge - # - TE_y: y-coordinate of trailing edge - # - TE_z: z-coordinate of trailing edge + # headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + # airfoil_id: 1 (since only one polar/interpolator is used) + # The kite is represented by 4 chordwise points at y = width/2, -width/2 and at y = 0. + # Chord positions from get_kite_points(s): P2 (center right), P3 (center left) + # Bridle/other points are omitted for simplicity. + # Units: meters # --------------------------------------------------------------- headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] data: - - [1, 0, 10, 0, 1, 10, 0] - - [2, 0, -10, 0, 1, -10, 0] + - [1, 0.0, 8.16/2, 3.15+4.9, 2.0, 8.16/2, 3.15+4.9] # Right tip chord (P2) + - [1, 0.0, -8.16/2, 3.15+4.9, 2.0, -8.16/2, 3.15+4.9] # Left tip chord (P3) + - [1, 0.0, 0.0, 4.9, 2.0, 0.0, 4.9] # Bridle attachment (P4/P5 merged, approx.) wing_airfoils: # --------------------------------------------------------------- - # headers: - # - airfoil_id: integer, unique identifier for the airfoil - # - type: one of [neuralfoil, breukels_regression, masure_regression, polars] - # - info_dict: dictionary with parameters depending on 'type' - # - # info_dict fields by type: - # - breukels_regression: - # t: Tube diameter non-dimensionalized by chord (required) - # kappa: Maximum camber height/magnitude, non-dimensionalized by chord (required) - # - neuralfoil: - # dat_file_path: Path to airfoil .dat file (x, y columns) - # model_size: NeuralFoil model size (e.g., "xxxlarge") - # xtr_lower: Lower transition location (0=forced, 1=free) - # xtr_upper: Upper transition location - # n_crit: Critical amplification factor (see guidelines below) - # n_crit guidelines: - # Sailplane: 12–14 - # Motorglider: 11–13 - # Clean wind tunnel: 10–12 - # Average wind tunnel: 9 (standard "e^9 method") - # Dirty wind tunnel: 4–8 - # - polars: - # csv_file_path: Path to polar CSV file (columns: alpha [rad], cl, cd, cm) - # - masure_regression: - # t, eta, kappa, delta, lamba, phi: Regression parameters - # - inviscid: - # no further data is required - # --------------------------------------------------------------- - alpha_range: [-10, 31, 0.5] # [deg], in this range the polars are calculated - reynolds: !!float 1e6 # Reynolds number + # Only one polar, which is interpolated in code; you may later link to a CSV file. + # --------------------------------------------------------------- + alpha_range: [-180, 180, 1] # deg + reynolds: 1e6 headers: [airfoil_id, type, info_dict] data: - - [1, polars, {csv_file_path: "polars/1.csv"}] - - [2, polars, {csv_file_path: "polars/2.csv"}] \ No newline at end of file + - [1, polars, {csv_file_path: "cl_cd_polar.csv"}] + +bridle_nodes: + # --------------------------------------------------------------- + # Use the points from get_kite_points(s), assuming: + # - P1: Bridle point + # - P2: right tip + # - P3: left tip + # - P4/P5: at width/2, -width/2, z = bridle height + # --------------------------------------------------------------- + headers: [id, x, y, z, type] + data: + - [1, 0.0, 0.0, 0.0, knot] # Bridle origin + - [2, 0.0, 8.16/2, 3.15+4.9, knot] # Right tip + - [3, 0.0, -8.16/2, 3.15+4.9, knot] # Left tip + - [4, 0.0, 8.16/2, 4.9, knot] # Bridle top right + - [5, 0.0, -8.16/2, 4.9, knot] # Bridle top left + +bridle_lines: + # --------------------------------------------------------------- + headers: [name, rest_length, diameter, material, density] + data: + - [bridle_main, 33.4, 0.0025, dyneema, 970] + +bridle_connections: + # --------------------------------------------------------------- + # Very simplified; you can expand as needed. Connects bridle origin to tips and bridle tops. + # headers: [name, ci, cj, ck] + data: + - [bridle_main, 1, 2, 0] + - [bridle_main, 1, 3, 0] + - [bridle_main, 1, 4, 0] + - [bridle_main, 1, 5, 0] + - [bridle_top, 4, 2, 0] + - [bridle_top, 5, 3, 0] + +tether: + # Tether from bridle origin (node 1) extending for l_tether meters + length: 50.0 + diameter: 0.004 + material: dyneema + density: 724.0 + segments: 14 diff --git a/data/pyramid_model/polars/1.csv b/data/pyramid_model/polars/1.csv index 618e39b9..d59a8817 100644 --- a/data/pyramid_model/polars/1.csv +++ b/data/pyramid_model/polars/1.csv @@ -1,71 +1,17 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.0249065318608897,-3.434761974054366e-21,-1.0732064541182402,0.0054067639622245 --9.5,0.0236873271741019,-3.285535810591269e-21,-1.0370727681402363,0.0058564293781756 --9.0,0.0225262393305432,-3.1355323293482928e-21,-0.9992907398617008,0.0062213900212979 --8.5,0.0214269325718191,-2.984782761608788e-21,-0.9599576821061372,0.0065104482864488 --8.0,0.0203930711395351,-2.833318338656105e-21,-0.9191709076970505,0.006732406568486 --7.5,0.0194283192752969,-2.6811702917735944e-21,-0.8770277294579452,0.0068960672622671 --7.0,0.01853634122071,-2.528369852244608e-21,-0.8336254602123256,0.0070102327626497 --6.5,0.0177208012173799,-2.3749482513524935e-21,-0.7890614127836962,0.0070837054644914 --6.0,0.0169853635069124,-2.2209367203806045e-21,-0.7434328999955613,0.0071252877626499 --5.5,0.0163336923309129,-2.06636649061229e-21,-0.6968372346714253,0.0071437820519827 --5.0,0.0157694519309871,-1.9112687933309017e-21,-0.6493717296347931,0.0071479907273476 --4.5,0.0152645128216272,-1.753587209885578e-21,-0.5997295153722275,0.0070196560505497 --4.0,0.01479533503566,-1.5927577702719893e-21,-0.5471734663994646,0.0066920925435352 --3.5,0.0143724670921928,-1.4310503787432801e-21,-0.4926555115837663,0.0062514609913727 --3.0,0.0140064575103327,-1.2707349395525959e-21,-0.4371275797923952,0.0057839221791311 --2.5,0.0137078548091868,-1.1140813569530825e-21,-0.3815415998926136,0.005375636891879 --2.0,0.0134872075078624,-9.63359535197884e-22,-0.326849500751684,0.0051127659146851 --1.5,0.0133110016081565,-8.173276016701202e-22,-0.2729636358104737,0.0049791802562241 --1.0,0.013154948085695,-6.747509165125449e-22,-0.219054658831915,0.0048810850331918 --0.5,0.0130434329203279,-5.379102331177564e-22,-0.1649619491663683,0.004788142192688 -0.0,0.0130008420919056,-4.090863048783536e-22,-0.1105248861641936,0.0046700136818125 -0.5,0.0130084720389809,-2.8680744793175213e-22,-0.0553123307395135,0.0044698279268781 -1.0,0.0130294722244102,-1.6963327644127745e-22,0.0004648326011776,0.0042125035054924 -1.5,0.013061008164498,-5.989149083839288e-23,0.0560041891189628,0.0039903875916971 -2.0,0.0131002453755492,4.009020844543824e-23,0.1105033240749248,0.0038958273595339 -2.5,0.0131856144242583,1.3202243421906704e-22,0.1645080620709747,0.0039708828537188 -3.0,0.0133528446868354,2.1941233713727904e-22,0.2188020358375745,0.0041687564292972 -3.5,0.0135950498938577,3.026270235375132e-22,0.2729395428286329,0.0044485087258047 -4.0,0.0139053437759025,3.820335997572082e-22,0.3264748804980587,0.0047692003827766 -4.5,0.0142768400635472,4.579991721338029e-22,0.3789623462997606,0.0050898920397485 -5.0,0.014702652487369,5.308908470047359e-22,0.4299562376876474,0.005369644336256 -5.5,0.0151758947779452,6.010757307074465e-22,0.4790108521156277,0.0055675179118344 -6.0,0.0156896806658533,6.6892092957937285e-22,0.5256804870376105,0.0056425734060194 -6.5,0.0163419408046433,7.3156512099210305e-22,0.5727462893873533,0.0056195012255208 -7.0,0.0172347131714976,7.87652640520907e-22,0.621930082521374,0.0055494832763917 -7.5,0.0183672724824413,8.3980908180874655e-22,0.6711971785277222,0.0054313174471822 -8.0,0.0197388934534996,8.906600384985838e-22,0.7185128894944469,0.0052638016264423 -8.5,0.0213488508006975,9.428311042333809e-22,0.7618425275095976,0.005045733702722 -9.0,0.0231964192400604,9.989478726560997e-22,0.7991514046612234,0.0047759115645714 -9.5,0.0252808734876132,1.0616359374097021e-21,0.8284048330373738,0.0044531331005404 -10.0,0.0276014882593813,1.133520892137151e-21,0.8475681247260978,0.0040761961991793 -10.5,0.0309750509211813,1.2264041564916665e-21,0.8593005363065593,0.0027629989121379 -11.0,0.0358184780617999,1.338964707337134e-21,0.8683373609449135,6.549186061715782e-05 -11.5,0.0415312382317165,1.4541444741325102e-21,0.8757579656096959,-0.0033664482125074 -12.0,0.0475127999814107,1.5548853863367533e-21,0.8826417172694425,-0.00688294456436 -12.5,0.0535718016380152,1.6355125000226549e-21,0.8901844683279677,-0.0103977924929974 -13.0,0.0601841135567709,1.707161865298813e-21,0.8977108722659604,-0.0143417322759933 -13.5,0.0677500523303184,1.7779919026778908e-21,0.9034934976672676,-0.0188403046397463 -14.0,0.0766699345512988,1.856161032672556e-21,0.9058049131157374,-0.0240190503106557 -14.5,0.0886600983806959,1.954578481220623e-21,0.8829547896813587,-0.0308720072112254 -15.0,0.1037898454535693,2.066176426506049e-21,0.8310805080016944,-0.0393733326507776 -15.5,0.1199889375736733,2.1691477174107125e-21,0.7751962010119524,-0.0481187464359375 -16.0,0.135187136544762,2.2416852028164918e-21,0.7403160016473408,-0.0557039683733306 -16.5,0.1490568222149959,2.2904946311980992e-21,0.7250755717384425,-0.0620365090305877 -17.0,0.1626441988491108,2.333059752262545e-21,0.7123987575512702,-0.0679085904012768 -17.5,0.1759397648757243,2.3637404167401576e-21,0.7037319686741754,-0.0732429994309288 -18.0,0.1889340187234538,2.376896475361265e-21,0.7005216146955101,-0.0779625230650747 -18.5,0.2016174588209165,2.366887778856196e-21,0.7042141052036259,-0.0819899482492452 -19.0,0.21398058359673,2.3280741779552778e-21,0.7162558497868752,-0.0852480619289713 -19.5,0.2260138914795117,2.2548155233888405e-21,0.738093258033609,-0.087659651049784 -20.0,0.237707880897879,2.1414716658872106e-21,0.7711727395321798,-0.0891475025572141 -20.5,0.2490530502804493,1.982402456180717e-21,0.816940703870939,-0.0896344033967926 -21.0,0.2600398980558399,1.7719677449996867e-21,0.8768435606382389,-0.0890431405140503 -21.5,0.2706589226526683,1.504527383074451e-21,0.9523277194224308,-0.0872965008545183 -22.0,0.280900622499552,1.174441221135335e-21,1.0448395898118663,-0.0843172713637273 -22.5,0.2907554960251083,7.760691099126683e-22,1.1558255813948983,-0.0800282389872084 -23.0,0.3002140416579548,3.0377090013677857e-22,1.2867321037598782,-0.0743521906704924 -23.5,0.3092667578267086,-2.480935574620052e-22,1.439005566495157,-0.0672119133591102 -24.0,0.3179041429599872,-8.851644121533548e-22,1.6140923791890878,-0.0585301939985927 -24.5,0.3261166954864083,-1.6130818132069429e-21,1.813438951430021,-0.048229819534471 \ No newline at end of file +alpha,Cl,Cd +-180.0,0.0,0.5 +-170.0,,0.5 +-160.0,0.5, +-140.0,,0.5 +-90.0,0.0,1.0 +-20.0,0.08,0.2 +-10.0,0.125, +-5.0,0.15, +0.0,0.2,0.1 +20.0,1.0,0.2 +40.0,1.0, +90.0,0.0,1.0 +140.0,,0.5 +160.0,-0.5, +170.0,,0.5 +180.0,0.0,0.5 diff --git a/data/pyramid_model/polars/2.csv b/data/pyramid_model/polars/2.csv deleted file mode 100644 index 1c856676..00000000 --- a/data/pyramid_model/polars/2.csv +++ /dev/null @@ -1,71 +0,0 @@ -alpha,Cd,Cs,Cl,Cm --10.0,0.1028496958630713,-4.970266483175547e-24,-0.4060358502753723,0.0550990480582689 --9.5,0.0971839746448208,-9.302148562803722e-24,-0.4438529313194241,0.0537303438488007 --9.0,0.0916177006701586,-2.1982895735540862e-23,-0.4741345054395691,0.0511424232336705 --8.5,0.0861488323939917,-4.2540159402165874e-23,-0.4977178511829077,0.047464579144667 --8.0,0.0807753282712272,-7.050159096345767e-23,-0.5154402470965408,0.0428261045135789 --7.5,0.0754951467567722,-1.0539484182019521e-22,-0.5281389717275694,0.0373562922721951 --7.0,0.070306246305534,-1.4674756337315738e-22,-0.536651303623094,0.0311844353523042 --6.5,0.0652065853724195,-1.9408740702312298e-22,-0.5418145213302155,0.0244398266856952 --6.0,0.0601941224123359,-2.4694202417087115e-22,-0.5444659033960346,0.0172517592041566 --5.5,0.0552668158801903,-3.048390662171807e-22,-0.5454427283676522,0.0097495258394774 --5.0,0.0504226242308899,-3.6730618456283053e-22,-0.5455822747921689,0.0020624195234464 --4.5,0.0454586930290803,-4.8527727098003185e-22,-0.5164772120836574,-0.0086109691796144 --4.0,0.0403444322748116,-6.841919162753791e-22,-0.4407589545148366,-0.0234630209344745 --3.5,0.0353361970760969,-9.25336320401227e-22,-0.3358228979207768,-0.0399508996529828 --3.0,0.0306903425409498,-1.1699966833099293e-21,-0.2190644381365483,-0.0555317692469881 --2.5,0.0266632237773835,-1.379459204953841e-21,-0.1078789709972217,-0.0676627936283392 --2.0,0.0235111958934114,-1.5150100852853154e-21,-0.0196618923378672,-0.0738011367088848 --1.5,0.0209681290308454,-1.593094370401261e-21,0.0469798152131813,-0.0758613643823688 --1.0,0.0187153462483676,-1.6568047141524793e-21,0.1073778817595349,-0.0774463151945054 --0.5,0.0169303820292961,-1.707398728122166e-21,0.1650449805640406,-0.0785455620350991 -0.0,0.0157907708569491,-1.7461340238935162e-21,0.2234937848895452,-0.079148677793954 -0.5,0.0150698972023441,-1.7793957856478226e-21,0.2837610810937657,-0.0794729390812699 -1.0,0.0144690585964555,-1.8093789788140737e-21,0.3439466460348425,-0.079729267044402 -1.5,0.0140576591125365,-1.831055886847014e-21,0.4031576387262576,-0.0798977013788872 -2.0,0.0139051028238406,-1.8393987932013843e-21,0.4605012181814928,-0.079958281780263 -2.5,0.0139674904323853,-1.831535360602796e-21,0.516687351824163,-0.0796996874903342 -3.0,0.0141466259946626,-1.8099484238780976e-21,0.57273004334973,-0.0790013079673623 -3.5,0.0144304686156374,-1.777643024633895e-21,0.6281925061794459,-0.0779792482315685 -4.0,0.0148069774002744,-1.7376242044767923e-21,0.6826379537345634,-0.0767496133031744 -4.5,0.0152641114535385,-1.6928970050133933e-21,0.7356295994363342,-0.0754285082024013 -5.0,0.0157898298803945,-1.646466467850302e-21,0.7867306567060111,-0.0741320379494707 -5.5,0.0163720917858072,-1.601337634594123e-21,0.8355043389648463,-0.0729763075646039 -6.0,0.0169988562747415,-1.5605155468514597e-21,0.8815138596340918,-0.0720774220680224 -6.5,0.0177994356563183,-1.5175949498829897e-21,0.9288116136606078,-0.0713170815492992 -7.0,0.0189149173688029,-1.4669336832133196e-21,0.979706268880088,-0.0705266061060592 -7.5,0.020350923210876,-1.412681429844948e-21,1.031145448047036,-0.0697465307706008 -8.0,0.0221130749812183,-1.358987872780374e-21,1.0800767739159551,-0.0690173905752227 -8.5,0.0242069944785106,-1.3100026950220965e-21,1.1234478692413494,-0.0683797205522237 -9.0,0.0266383035014336,-1.2698755795726137e-21,1.158206356777722,-0.0678740557339022 -9.5,0.029412623848668,-1.2427562094344249e-21,1.181299859279576,-0.067540931152557 -10.0,0.0325355773188947,-1.232794267610029e-21,1.1896759995014154,-0.0674208818404867 -10.5,0.0372054744229639,-1.2470041563884788e-21,1.189133433306183,-0.0692679925714252 -11.0,0.0441832190788797,-1.2828706185025538e-21,1.1875712414485422,-0.0739531725836439 -11.5,0.0528183231960532,-1.3302488476203426e-21,1.1850876840205773,-0.0801921936062471 -12.0,0.0624602986838954,-1.3789940374099341e-21,1.1817810211143729,-0.0867008273683394 -12.5,0.0742566292803452,-1.433366612863428e-21,1.1679087624369973,-0.0941403849694034 -13.0,0.088907203547694,-1.4986779338953496e-21,1.1392200860184896,-0.1032402342413439 -13.5,0.1050901406318811,-1.5663595965574256e-21,1.104050754435393,-0.1128182320118979 -14.0,0.1214835596788457,-1.6278431969013822e-21,1.0707365302642493,-0.1216922351088023 -14.5,0.1393968397552119,-1.6778081057743264e-21,1.0407056899781189,-0.1293305571068038 -15.0,0.1590650543975536,-1.722268328504924e-21,1.0096896000655085,-0.1364631706963764 -15.5,0.1775548644567351,-1.7696574128672416e-21,0.9774786581261288,-0.1438004213788477 -16.0,0.1919329307836206,-1.8284089066353454e-21,0.9438632617596906,-0.1520526546555453 -16.5,0.203232606090166,-1.900079491549716e-21,0.9092321872293124,-0.1611787571831155 -17.0,0.2143889288649201,-1.980597122465185e-21,0.8740961053107327,-0.1706707679195053 -17.5,0.2253210886236354,-2.0699522568273426e-21,0.8384282553725938,-0.180538760817993 -18.0,0.2359482748820647,-2.168135352081781e-21,0.8022018767835378,-0.190792809831857 -18.5,0.2461896771559607,-2.275136865674092e-21,0.7653902089122069,-0.2014429889143758 -19.0,0.2559644849610761,-2.3909472550498657e-21,0.7279664911272431,-0.2124993720188276 -19.5,0.2651918878131636,-2.5155569776546938e-21,0.6899039627972886,-0.2239720330984911 -20.0,0.273791075227976,-2.6489564909341693e-21,0.6511758632909855,-0.2358710461066446 -20.5,0.281681236721266,-2.7911362523338815e-21,0.6117554319769761,-0.2482064849965665 -21.0,0.2887815618087863,-2.942086719299423e-21,0.5716159082239023,-0.2609884237215353 -21.5,0.2950112400062896,-3.101798349276385e-21,0.5307305314004064,-0.2742269362348293 -22.0,0.3002894608295286,-3.2702615997103588e-21,0.4890725408751303,-0.287932096489727 -22.5,0.304535413794256,-3.447466928046934e-21,0.4466151760167164,-0.3021139784395067 -23.0,0.3076682884162247,-3.633404791731706e-21,0.4033316761938067,-0.316782656037447 -23.5,0.3096072742111871,-3.828065648210263e-21,0.3591952807750433,-0.3319482032368263 -24.0,0.3102715606948962,-4.031439954928197e-21,0.3141792291290685,-0.3476206939909228 -24.5,0.3095803373831047,-4.2435181693311005e-21,0.2682567606245242,-0.3638102022530151 \ No newline at end of file diff --git a/data/ram_air_kite_body.obj b/data/ram_air_kite/ram_air_kite_body.obj similarity index 100% rename from data/ram_air_kite_body.obj rename to data/ram_air_kite/ram_air_kite_body.obj diff --git a/data/ram_air_kite_foil.dat b/data/ram_air_kite/ram_air_kite_foil.dat similarity index 100% rename from data/ram_air_kite_foil.dat rename to data/ram_air_kite/ram_air_kite_foil.dat diff --git a/data/ram_air_kite_foil_cd_polar.csv b/data/ram_air_kite/ram_air_kite_foil_cd_polar.csv similarity index 100% rename from data/ram_air_kite_foil_cd_polar.csv rename to data/ram_air_kite/ram_air_kite_foil_cd_polar.csv diff --git a/data/ram_air_kite_foil_cl_polar.csv b/data/ram_air_kite/ram_air_kite_foil_cl_polar.csv similarity index 100% rename from data/ram_air_kite_foil_cl_polar.csv rename to data/ram_air_kite/ram_air_kite_foil_cl_polar.csv diff --git a/data/ram_air_kite_foil_cm_polar.csv b/data/ram_air_kite/ram_air_kite_foil_cm_polar.csv similarity index 100% rename from data/ram_air_kite_foil_cm_polar.csv rename to data/ram_air_kite/ram_air_kite_foil_cm_polar.csv diff --git a/data/vsm_settings.yaml b/data/ram_air_kite/vsm_settings.yaml similarity index 100% rename from data/vsm_settings.yaml rename to data/ram_air_kite/vsm_settings.yaml diff --git a/data/vsm_settings_dual.yaml b/data/ram_air_kite/vsm_settings_dual.yaml similarity index 100% rename from data/vsm_settings_dual.yaml rename to data/ram_air_kite/vsm_settings_dual.yaml diff --git a/examples/bench.jl b/examples/bench.jl index 87332aec..371958f2 100644 --- a/examples/bench.jl +++ b/examples/bench.jl @@ -56,7 +56,7 @@ println("Rectangular wing, solve:") @time solve(vsm_solver, body_aero, nothing) # Create wing geometry -wing = RamAirWing("data/ram_air_kite_body.obj", "data/ram_air_kite_foil.dat"; prn=false) +wing = RamAirWing("data/ram_air_kite/ram_air_kite_body.obj", "data/ram_air_kite/ram_air_kite_foil.dat"; prn=false) body_aero = BodyAerodynamics([wing]) # Create solvers diff --git a/examples/cleanup.jl b/examples/cleanup.jl index ce0d248d..c1d8f1cc 100644 --- a/examples/cleanup.jl +++ b/examples/cleanup.jl @@ -2,9 +2,9 @@ # delete the generated polars # it is useful if you want to benchmark the polar generation or if you have changed parameters -file1="data/ram_air_kite_foil_cl_polar.csv" -file2="data/ram_air_kite_foil_cd_polar.csv" -file3="data/ram_air_kite_foil_cm_polar.csv" +file1="data/ram_air_kite/ram_air_kite_foil_cl_polar.csv" +file2="data/ram_air_kite/ram_air_kite_foil_cd_polar.csv" +file3="data/ram_air_kite/ram_air_kite_foil_cm_polar.csv" isfile(file1) && rm(file1) isfile(file2) && rm(file2) isfile(file3) && rm(file3) diff --git a/examples/pyramid_model.jl b/examples/pyramid_model.jl index dccd5c56..44030949 100644 --- a/examples/pyramid_model.jl +++ b/examples/pyramid_model.jl @@ -30,72 +30,72 @@ va = wind_speed * [ ] set_va!(body_aero, va) -# --- Create and run VSM solver --- -solver = Solver(body_aero; - aerodynamic_model_type=VSM, - is_with_artificial_damping=false, - rtol=1e-5, - solver_type=NONLIN -) - -# One can run the solver seperately, given back a Dict{String, Any} -solver = Solver(body_aero; density=air_density) -solve!(solver, body_aero) -forces = solver.sol.force -println("\nType of solver: ", typeof(solver), " Type of forces: ", typeof(forces)) - -# Better to use the VortexStepMethod.solve method, returns a dictionary with the results -results = VortexStepMethod.solve(solver, body_aero; log=true) -println("Type of results: ", typeof(results)) - - -# --- Run over an alpha sweep --- -# using Plots # Add this at the top if you want to plot -alphas = 1:10 -f_xs = Float64[] # Fx over alpha sweep -f_ys = Float64[] # Fy over alpha sweep -f_zs = Float64[] # Fz over alpha sweep -m_xs = Float64[] # Mx over alpha sweep -m_ys = Float64[] # My over alpha sweep -m_zs = Float64[] # Mz over alpha sweep - -for alpha in alphas - local_α = deg2rad(alpha) - local_β = deg2rad(sideslip_deg) - local_va = wind_speed * [ - cos(local_α)*cos(local_β), - sin(local_β), - sin(local_α)*cos(local_β) - ] - set_va!(body_aero, local_va) - - solve!(solver, body_aero) - results_i = VortexStepMethod.solve(solver, body_aero; log=true) - - push!(f_xs, results_i["Fx"]) - push!(f_ys, results_i["Fy"]) - push!(f_zs, results_i["Fz"]) - push!(m_xs, results_i["Mx"]) - push!(m_ys, results_i["My"]) - push!(m_zs, results_i["Mz"]) - -end - - -# --- Plot results: true multi-row plotx style as in simple_lin_model.jl --- -p = plotx( - alphas, - f_xs, - f_ys, - f_zs, - m_xs, - m_ys, - m_zs; - ylabels=["Fx [N]", "Fy [N]", "Fz [N]", "Mx [Nm]", "My [Nm]", "Mz [Nm]"], - xlabel="alpha [deg]", - fig="Aerodynamic Forces and Moments" -) -display(p) +# # --- Create and run VSM solver --- +# solver = Solver(body_aero; +# aerodynamic_model_type=VSM, +# is_with_artificial_damping=false, +# rtol=1e-5, +# solver_type=NONLIN +# ) + +# # One can run the solver seperately, given back a Dict{String, Any} +# solver = Solver(body_aero; density=air_density) +# solve!(solver, body_aero) +# forces = solver.sol.force +# println("\nType of solver: ", typeof(solver), " Type of forces: ", typeof(forces)) + +# # Better to use the VortexStepMethod.solve method, returns a dictionary with the results +# results = VortexStepMethod.solve(solver, body_aero; log=true) +# println("Type of results: ", typeof(results)) + + +# # --- Run over an alpha sweep --- +# # using Plots # Add this at the top if you want to plot +# alphas = 1:10 +# f_xs = Float64[] # Fx over alpha sweep +# f_ys = Float64[] # Fy over alpha sweep +# f_zs = Float64[] # Fz over alpha sweep +# m_xs = Float64[] # Mx over alpha sweep +# m_ys = Float64[] # My over alpha sweep +# m_zs = Float64[] # Mz over alpha sweep + +# for alpha in alphas +# local_α = deg2rad(alpha) +# local_β = deg2rad(sideslip_deg) +# local_va = wind_speed * [ +# cos(local_α)*cos(local_β), +# sin(local_β), +# sin(local_α)*cos(local_β) +# ] +# set_va!(body_aero, local_va) + +# solve!(solver, body_aero) +# results_i = VortexStepMethod.solve(solver, body_aero; log=true) + +# push!(f_xs, results_i["Fx"]) +# push!(f_ys, results_i["Fy"]) +# push!(f_zs, results_i["Fz"]) +# push!(m_xs, results_i["Mx"]) +# push!(m_ys, results_i["My"]) +# push!(m_zs, results_i["Mz"]) + +# end + + +# # --- Plot results: true multi-row plotx style as in simple_lin_model.jl --- +# p = plotx( +# alphas, +# f_xs, +# f_ys, +# f_zs, +# m_xs, +# m_ys, +# m_zs; +# ylabels=["Fx [N]", "Fy [N]", "Fz [N]", "Mx [Nm]", "My [Nm]", "Mz [Nm]"], +# xlabel="alpha [deg]", +# fig="Aerodynamic Forces and Moments" +# ) +# display(p) # Using plotting modules, to create more comprehensive plots @@ -116,36 +116,36 @@ PLOT && plot_geometry( use_tex=USE_TEX ) -# Plotting polars -PLOT && plot_polars( - [solver], - [body_aero], - ["VSM from Ram Air Kite OBJ and DAT file"], - angle_range=range(0, 20, length=20), - angle_type="angle_of_attack", - angle_of_attack=5, - side_slip=0, - v_a=10, - title="pyramid $(wing.n_panels)_distribution_$(wing.spanwise_distribution)", - data_type=".pdf", - is_save=false, - is_show=true, - use_tex=USE_TEX -) - -# Plotting spanwise distributions -body_y_coordinates = [panel.aero_center[2] for panel in body_aero.panels] - -PLOT && plot_distribution( - [body_y_coordinates], - [results], - ["VSM"]; - title="CAD_spanwise_distributions_alpha_$(round(angle_of_attack_deg, digits=1))_delta_$(round(sideslip_deg, digits=1))_yaw_$(round(yaw_rate, digits=1))_v_a_$(round(wind_speed, digits=1))", - data_type=".pdf", - is_save=false, - is_show=true, - use_tex=USE_TEX -) +# # Plotting polars +# PLOT && plot_polars( +# [solver], +# [body_aero], +# ["VSM from Ram Air Kite OBJ and DAT file"], +# angle_range=range(0, 20, length=20), +# angle_type="angle_of_attack", +# angle_of_attack=5, +# side_slip=0, +# v_a=10, +# title="pyramid $(wing.n_panels)_distribution_$(wing.spanwise_distribution)", +# data_type=".pdf", +# is_save=false, +# is_show=true, +# use_tex=USE_TEX +# ) + +# # Plotting spanwise distributions +# body_y_coordinates = [panel.aero_center[2] for panel in body_aero.panels] + +# PLOT && plot_distribution( +# [body_y_coordinates], +# [results], +# ["VSM"]; +# title="CAD_spanwise_distributions_alpha_$(round(angle_of_attack_deg, digits=1))_delta_$(round(sideslip_deg, digits=1))_yaw_$(round(yaw_rate, digits=1))_v_a_$(round(wind_speed, digits=1))", +# data_type=".pdf", +# is_save=false, +# is_show=true, +# use_tex=USE_TEX +# ) nothing \ No newline at end of file diff --git a/examples/ram_air_kite.jl b/examples/ram_air_kite.jl index ab30b027..1aee03ca 100644 --- a/examples/ram_air_kite.jl +++ b/examples/ram_air_kite.jl @@ -9,7 +9,7 @@ DEFORM = false LINEARIZE = false # Create wing geometry -wing = RamAirWing("data/ram_air_kite_body.obj", "data/ram_air_kite_foil.dat"; prn=PRN) +wing = RamAirWing("data/ram_air_kite/ram_air_kite_body.obj", "data/ram_air_kite/ram_air_kite_foil.dat"; prn=PRN) body_aero = BodyAerodynamics([wing];) println("First init") @time VortexStepMethod.reinit!(body_aero) diff --git a/src/settings.jl b/src/settings.jl index 56e6694b..80ffeaa1 100644 --- a/src/settings.jl +++ b/src/settings.jl @@ -48,7 +48,7 @@ function vs(filename) # But handle special fields manually due to enum conversion needs vsm_settings = VSMSettings() - # Convert condition settings using StructMapping + # Convert condition settings using StructMapping (if present) if haskey(data, "condition") vsm_settings.condition = convertdict(ConditionSettings, data["condition"]) end diff --git a/test/test_plotting.jl b/test/test_plotting.jl index e3f6c7e2..7ae0b38b 100644 --- a/test/test_plotting.jl +++ b/test/test_plotting.jl @@ -5,8 +5,8 @@ using Test if !@isdefined ram_wing body_path = joinpath(tempdir(), "ram_air_kite_body.obj") foil_path = joinpath(tempdir(), "ram_air_kite_foil.dat") - cp("data/ram_air_kite_body.obj", body_path; force=true) - cp("data/ram_air_kite_foil.dat", foil_path; force=true) + cp("data/ram_air_kite/ram_air_kite_body.obj", body_path; force=true) + cp("data/ram_air_kite/ram_air_kite_foil.dat", foil_path; force=true) ram_wing = RamAirWing(body_path, foil_path; alpha_range=deg2rad.(-1:1), delta_range=deg2rad.(-1:1)) end diff --git a/test/test_results.jl b/test/test_results.jl index fd3470fc..762b6d17 100644 --- a/test/test_results.jl +++ b/test/test_results.jl @@ -5,10 +5,22 @@ using Test using Logging if !@isdefined ram_wing + # Use absolute paths to ensure files are found + data_dir = joinpath(dirname(@__DIR__), "data", "ram_air_kite") body_path = joinpath(tempdir(), "ram_air_kite_body.obj") foil_path = joinpath(tempdir(), "ram_air_kite_foil.dat") - cp("data/ram_air_kite_body.obj", body_path; force=true) - cp("data/ram_air_kite_foil.dat", foil_path; force=true) + + body_src = joinpath(data_dir, "ram_air_kite_body.obj") + foil_src = joinpath(data_dir, "ram_air_kite_foil.dat") + + # Check if source files exist before copying + if isfile(body_src) && isfile(foil_src) + cp(body_src, body_path; force=true) + cp(foil_src, foil_path; force=true) + else + error("Required data files not found: $body_src or $foil_src") + end + ram_wing = RamAirWing(body_path, foil_path; alpha_range=deg2rad.(-1:1), delta_range=deg2rad.(-1:1)) end diff --git a/test/test_settings.jl b/test/test_settings.jl index 06cde0ea..214c333d 100644 --- a/test/test_settings.jl +++ b/test/test_settings.jl @@ -7,12 +7,12 @@ using VortexStepMethod using Test @testset "Test settings.jl" begin - vss = vs("vsm_settings_dual.yaml") + vss = vs("ram_air_kite/vsm_settings_dual.yaml") @test vss isa VSMSettings @test vss.solver_settings isa SolverSettings @test vss.wings isa Vector{WingSettings} @test length(vss.wings) == 2 io = IOBuffer(repr(vss)) - @test countlines(io) == 32 + @test countlines(io) == 40 # Updated to match new output format end nothing From 29f372da8295a216155b9e7eb2ef6138284b6ea4 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Wed, 6 Aug 2025 08:34:12 +0200 Subject: [PATCH 15/26] #185 adding a working pyramid model example --- data/pyramid_model/polars/1.csv | 17 -- .../polars/V3_kite_midspan_airfoil_polar.csv | 71 ++++++++ data/pyramid_model/vsm_settings.yaml | 110 +++++++---- .../{geometry.yaml => wing_geometry.yaml} | 18 +- examples/pyramid_model.jl | 171 ++++++------------ 5 files changed, 214 insertions(+), 173 deletions(-) delete mode 100644 data/pyramid_model/polars/1.csv create mode 100644 data/pyramid_model/polars/V3_kite_midspan_airfoil_polar.csv rename data/pyramid_model/{geometry.yaml => wing_geometry.yaml} (76%) diff --git a/data/pyramid_model/polars/1.csv b/data/pyramid_model/polars/1.csv deleted file mode 100644 index d59a8817..00000000 --- a/data/pyramid_model/polars/1.csv +++ /dev/null @@ -1,17 +0,0 @@ -alpha,Cl,Cd --180.0,0.0,0.5 --170.0,,0.5 --160.0,0.5, --140.0,,0.5 --90.0,0.0,1.0 --20.0,0.08,0.2 --10.0,0.125, --5.0,0.15, -0.0,0.2,0.1 -20.0,1.0,0.2 -40.0,1.0, -90.0,0.0,1.0 -140.0,,0.5 -160.0,-0.5, -170.0,,0.5 -180.0,0.0,0.5 diff --git a/data/pyramid_model/polars/V3_kite_midspan_airfoil_polar.csv b/data/pyramid_model/polars/V3_kite_midspan_airfoil_polar.csv new file mode 100644 index 00000000..8e996699 --- /dev/null +++ b/data/pyramid_model/polars/V3_kite_midspan_airfoil_polar.csv @@ -0,0 +1,71 @@ +alpha,Cd,Cs,Cl,Cm +-10.0,0.1759893858334057,2.963819078393553e-21,-0.7493726713784946,0.2323775006207747 +-9.5,0.16289734924603438,2.7877286866584314e-21,-0.6924217529040287,0.2150382675337481 +-9.0,0.1504301874457461,2.6166544368792525e-21,-0.6371323632116463,0.1982607529225381 +-8.5,0.13862765245364775,2.4505707167459407e-21,-0.583498032661642,0.182046261914037 +-8.0,0.1275294962908461,2.2894519139484196e-21,-0.5315122916143107,0.16639609963513724 +-7.5,0.11717547097844788,2.133272416176612e-21,-0.4811686704299467,0.15131157121273117 +-7.0,0.10760532853756002,1.9820066111204418e-21,-0.4324606994688453,0.13679398177371113 +-6.5,0.09885882098928928,1.8356288864698326e-21,-0.38538190909130093,0.12284463644496953 +-6.0,0.09097570035474245,1.694113629914708e-21,-0.3399258296576083,0.10946484035339869 +-5.5,0.08399571865502635,1.557435229144991e-21,-0.2960859915280623,0.09665589862589102 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+22.5,0.3462258406278082,-7.210927738558214e-22,1.0418506907541978,-0.17838813341813575 +23.0,0.35623515262436534,-7.213063626837044e-22,1.044574269637424,-0.17967706251871235 +23.5,0.36619361005701967,-7.21886103787958e-22,1.0474653261573934,-0.18089150083937203 +24.0,0.3761008243741252,-7.230150733067677e-22,1.0505088866722323,-0.18202480456295017 +24.5,0.38595640702403533,-7.248763473783189e-22,1.0536899775400672,-0.18307032987228236 diff --git a/data/pyramid_model/vsm_settings.yaml b/data/pyramid_model/vsm_settings.yaml index 5ae66dc9..93ba2ca8 100644 --- a/data/pyramid_model/vsm_settings.yaml +++ b/data/pyramid_model/vsm_settings.yaml @@ -1,36 +1,80 @@ -Model: - VSM: Vortex Step Method - LLT: Lifting Line Theory -PanelDistribution: - LINEAR: Linear distribution - COSINE: Cosine distribution - COSINE_VAN_GARREL: van Garrel cosine distribution - SPLIT_PROVIDED: Split provided sections - UNCHANGED: Keep original sections -InitialGammaDistribution: - ELLIPTIC: Elliptic distribution - ZEROS: Constant distribution +# ============================================================================= +# VSM Settings Configuration File +# ============================================================================= +# +# This YAML file configures the Vortex Step Method (VSM) aerodynamic solver +# for wing analysis. All simulation parameters are centralized here. +# +# FILE STRUCTURE: +# ├── condition: Flight conditions (wind speed, angles, rates) +# ├── wings: Wing geometry and discretization settings +# └── solver_settings: Numerical solver parameters and convergence criteria +# +# AERODYNAMIC MODELS: +# VSM: Vortex Step Method - Full 3D potential flow with wake modeling +# LLT: Lifting Line Theory - Classical 1D approach for high aspect ratios +# +# PANEL DISTRIBUTIONS: +# LINEAR: Uniform panel spacing along wingspan +# COSINE: Cosine clustering (more panels at tips) +# COSINE_VAN_GARREL: Van Garrel's modified cosine distribution +# SPLIT_PROVIDED: Use predefined section splits from geometry +# UNCHANGED: Preserve original geometry discretization +# +# INITIAL CIRCULATION DISTRIBUTIONS: +# ELLIPTIC: Elliptical distribution (optimal for efficiency) +# ZEROS: Start with zero circulation (cold start) +# +# SOLVER TYPES: +# LOOP: Iterative fixed-point solver +# NEWTON: Newton-Raphson nonlinear solver +# +# USAGE NOTES: +# - n_panels should be divisible by n_groups for proper load balancing +# - Higher n_panels improves accuracy but increases computation time +# - Lower relaxation_factor if convergence issues occur +# Define the flight state for the aerodynamic analysis +condition: + wind_speed: 10.0 # [m/s] Free stream velocity magnitude + alpha: 5.0 # [°] Angle of attack (pitch angle relative to flow) + beta: 0.0 # [°] Sideslip angle (yaw angle relative to flow) + yaw_rate: 0.0 # [°/s] Yaw rate (for dynamic analysis, 0 for static) + +# Define wing geometry files and discretization parameters wings: - - name: main_wing - n_panels: 40 - n_groups: 40 - spanwise_panel_distribution: LINEAR - spanwise_direction: [0.0, 1.0, 0.0] - remove_nan: true + - name: V3_Kite # Wing identifier for output labeling + geometry_file: data/pyramid_model/wing_geometry.yaml + n_panels: 2 # Total number of panels along wingspan + n_groups: 1 # Number of panel groups (must divide n_panels) + spanwise_panel_distribution: LINEAR # Panel spacing algorithm + spanwise_direction: [0.0, 1.0, 0.0] # Unit vector defining wingspan direction + remove_nan: true # Remove NaN values from polar data + +# Numerical method settings and convergence criteria solver_settings: - n_panels: 40 - n_groups: 40 - aerodynamic_model_type: VSM - density: 1.225 # air density [kg/m³] - max_iterations: 1500 - rtol: 1e-5 # relative error [-] - tol_reference_error: 0.001 - relaxation_factor: 0.03 # relaxation factor for convergence - artificial_damping: false # whether to apply artificial damping - k2: 0.1 # artificial damping parameter - k4: 0.0 # artificial damping parameter - type_initial_gamma_distribution: ELLIPTIC - core_radius_fraction: 1e-20 - mu: 1.81e-5 # dynamic viscosity [N·s/m²] - calc_only_f_and_gamma: false # whether to only output f and gamma + # --- Core Aerodynamic Model --- + aerodynamic_model_type: VSM # VSM=3D vortex method, LLT=lifting line theory + solver_type: LOOP # LOOP=fixed-point iteration, NEWTON=Newton-Raphson + + # --- Physical Properties --- + density: 1.225 # [kg/m³] Air density (ISA sea level) + mu: 1.81e-5 # [N·s/m²] Dynamic viscosity (ISA sea level) + + # --- Convergence Control --- + max_iterations: 5000 # Maximum solver iterations before timeout + rtol: 1e-6 # Relative tolerance for convergence + tol_reference_error: 0.001 # Reference error tolerance + relaxation_factor: 0.01 # [0.001-0.1] Under-relaxation for stability + + # --- Numerical Stability --- + artificial_damping: false # Enable artificial damping for unstable cases + k2: 0.1 # 2nd-order damping coefficient + k4: 0.0 # 4th-order damping coefficient + core_radius_fraction: 1e-20 # Vortex core radius (fraction of chord) + + # --- Initial Conditions --- + type_initial_gamma_distribution: ELLIPTIC # Starting circulation distribution + + # --- Output Control --- + calc_only_f_and_gamma: false # true=compute only forces & circulation diff --git a/data/pyramid_model/geometry.yaml b/data/pyramid_model/wing_geometry.yaml similarity index 76% rename from data/pyramid_model/geometry.yaml rename to data/pyramid_model/wing_geometry.yaml index dfbb71bb..74e62c61 100644 --- a/data/pyramid_model/geometry.yaml +++ b/data/pyramid_model/wing_geometry.yaml @@ -11,9 +11,9 @@ wing_sections: # --------------------------------------------------------------- headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] data: - - [1, 0.0, 8.16/2, 3.15+4.9, 2.0, 8.16/2, 3.15+4.9] # Right tip chord (P2) - - [1, 0.0, -8.16/2, 3.15+4.9, 2.0, -8.16/2, 3.15+4.9] # Left tip chord (P3) - - [1, 0.0, 0.0, 4.9, 2.0, 0.0, 4.9] # Bridle attachment (P4/P5 merged, approx.) + - [1, 0.0, 4.08, 4.9, 2.0, 4.08, 4.9] # Right tip chord (P2) + - [1, 0.0, -4.08, 4.9, 2.0, -4.08, 4.9] # Left tip chord (P3) + - [1, 0.0, 0.0, 8.05, 2.0, 0.0, 8.05] # Bridle attachment (P4/P5 merged, approx.) wing_airfoils: # --------------------------------------------------------------- @@ -23,7 +23,7 @@ wing_airfoils: reynolds: 1e6 headers: [airfoil_id, type, info_dict] data: - - [1, polars, {csv_file_path: "cl_cd_polar.csv"}] + - [1, polars, {csv_file_path: "polars/V3_kite_midspan_airfoil_polar.csv"}] bridle_nodes: # --------------------------------------------------------------- @@ -35,11 +35,11 @@ bridle_nodes: # --------------------------------------------------------------- headers: [id, x, y, z, type] data: - - [1, 0.0, 0.0, 0.0, knot] # Bridle origin - - [2, 0.0, 8.16/2, 3.15+4.9, knot] # Right tip - - [3, 0.0, -8.16/2, 3.15+4.9, knot] # Left tip - - [4, 0.0, 8.16/2, 4.9, knot] # Bridle top right - - [5, 0.0, -8.16/2, 4.9, knot] # Bridle top left + - [1, 0.0, 0.0, 0.0, knot] # Bridle origin + - [2, 0.0, 4.08, 8.05, knot] # Right tip + - [3, 0.0, -4.08, 8.05, knot] # Left tip + - [4, 0.0, 4.08, 4.9, knot] # Bridle top right + - [5, 0.0, -4.08, 4.9, knot] # Bridle top left bridle_lines: # --------------------------------------------------------------- diff --git a/examples/pyramid_model.jl b/examples/pyramid_model.jl index 44030949..45e72b86 100644 --- a/examples/pyramid_model.jl +++ b/examples/pyramid_model.jl @@ -2,108 +2,69 @@ using LinearAlgebra using VortexStepMethod using ControlPlots -# --- User-specified parameters --- -wind_speed = 10.0 # [m/s] -angle_of_attack_deg = 5.0 # [deg] -sideslip_deg = 0.0 -yaw_rate = 0.0 # [rad/s] (not used in static analysis) -air_density = 1.225 # [kg/m^3] Air density at sea level project_dir = dirname(dirname(pathof(VortexStepMethod))) # Go up one level from src to project root -yaml_geometry_path = joinpath(project_dir, "data", "pyramid_model", "geometry.yaml") -println("=== Static Aerodynamic Analysis (VSM) ===") -println("Wind speed: $wind_speed m/s") -println("Angle of attack: $angle_of_attack_deg deg") -println("Sideslip: $sideslip_deg deg") +# Load VSM settings from YAML configuration file +settings = vs("pyramid_model/vsm_settings.yaml") -# Create wing geometry from YAML (following RamAirWing pattern) -wing = YamlWing(yaml_geometry_path; n_panels=20, spanwise_distribution=LINEAR) +# Extract flight conditions from settings +wind_speed = settings.condition.wind_speed +angle_of_attack_deg = settings.condition.alpha +sideslip_deg = settings.condition.beta +yaw_rate = settings.condition.yaw_rate + +# Create wing, body_aero, and solver objects using settings +wing = YamlWing(settings.wings[1].geometry_file; + n_panels=settings.wings[1].n_panels, + n_groups=settings.wings[1].n_groups, + spanwise_distribution=settings.wings[1].spanwise_panel_distribution +) body_aero = BodyAerodynamics([wing]) +solver = Solver(body_aero; + aerodynamic_model_type=settings.solver_settings.aerodynamic_model_type, + density=settings.solver_settings.density, + max_iterations=settings.solver_settings.max_iterations, + rtol=settings.solver_settings.rtol, + relaxation_factor=settings.solver_settings.relaxation_factor, + core_radius_fraction=settings.solver_settings.core_radius_fraction, +) -# --- Set apparent wind vector in body axes --- -α = deg2rad(angle_of_attack_deg) -β = deg2rad(sideslip_deg) -va = wind_speed * [ +# Set flight conditions +α = deg2rad(settings.condition.alpha) +β = deg2rad(settings.condition.beta) +va = settings.condition.wind_speed * [ cos(α)*cos(β), # X_b (forward) sin(β), # Y_b (right) sin(α)*cos(β) # Z_b (down) ] set_va!(body_aero, va) -# # --- Create and run VSM solver --- -# solver = Solver(body_aero; -# aerodynamic_model_type=VSM, -# is_with_artificial_damping=false, -# rtol=1e-5, -# solver_type=NONLIN -# ) - -# # One can run the solver seperately, given back a Dict{String, Any} -# solver = Solver(body_aero; density=air_density) -# solve!(solver, body_aero) -# forces = solver.sol.force -# println("\nType of solver: ", typeof(solver), " Type of forces: ", typeof(forces)) - -# # Better to use the VortexStepMethod.solve method, returns a dictionary with the results -# results = VortexStepMethod.solve(solver, body_aero; log=true) -# println("Type of results: ", typeof(results)) - - -# # --- Run over an alpha sweep --- -# # using Plots # Add this at the top if you want to plot -# alphas = 1:10 -# f_xs = Float64[] # Fx over alpha sweep -# f_ys = Float64[] # Fy over alpha sweep -# f_zs = Float64[] # Fz over alpha sweep -# m_xs = Float64[] # Mx over alpha sweep -# m_ys = Float64[] # My over alpha sweep -# m_zs = Float64[] # Mz over alpha sweep - -# for alpha in alphas -# local_α = deg2rad(alpha) -# local_β = deg2rad(sideslip_deg) -# local_va = wind_speed * [ -# cos(local_α)*cos(local_β), -# sin(local_β), -# sin(local_α)*cos(local_β) -# ] -# set_va!(body_aero, local_va) - -# solve!(solver, body_aero) -# results_i = VortexStepMethod.solve(solver, body_aero; log=true) - -# push!(f_xs, results_i["Fx"]) -# push!(f_ys, results_i["Fy"]) -# push!(f_zs, results_i["Fz"]) -# push!(m_xs, results_i["Mx"]) -# push!(m_ys, results_i["My"]) -# push!(m_zs, results_i["Mz"]) - -# end - - -# # --- Plot results: true multi-row plotx style as in simple_lin_model.jl --- -# p = plotx( -# alphas, -# f_xs, -# f_ys, -# f_zs, -# m_xs, -# m_ys, -# m_zs; -# ylabels=["Fx [N]", "Fy [N]", "Fz [N]", "Mx [Nm]", "My [Nm]", "Mz [Nm]"], -# xlabel="alpha [deg]", -# fig="Aerodynamic Forces and Moments" -# ) -# display(p) - +# Run the solver +results = VortexStepMethod.solve(solver, body_aero; log=true) # Using plotting modules, to create more comprehensive plots PLOT = true USE_TEX = false +# Plotting polars +PLOT && plot_polars( + [solver], + [body_aero], + ["VSM Pyramid Model"], + angle_range=range(-5, 25, length=30), + angle_type="angle_of_attack", + angle_of_attack=angle_of_attack_deg, + side_slip=sideslip_deg, + v_a=wind_speed, + title="$(wing.n_panels)_panels_$(wing.spanwise_distribution)_pyramid_model", + data_type=".pdf", + is_save=false, + is_show=true, + use_tex=USE_TEX +) # Plotting geometry +results = VortexStepMethod.solve(solver, body_aero; log=true) PLOT && plot_geometry( body_aero, ""; @@ -116,36 +77,18 @@ PLOT && plot_geometry( use_tex=USE_TEX ) -# # Plotting polars -# PLOT && plot_polars( -# [solver], -# [body_aero], -# ["VSM from Ram Air Kite OBJ and DAT file"], -# angle_range=range(0, 20, length=20), -# angle_type="angle_of_attack", -# angle_of_attack=5, -# side_slip=0, -# v_a=10, -# title="pyramid $(wing.n_panels)_distribution_$(wing.spanwise_distribution)", -# data_type=".pdf", -# is_save=false, -# is_show=true, -# use_tex=USE_TEX -# ) - -# # Plotting spanwise distributions -# body_y_coordinates = [panel.aero_center[2] for panel in body_aero.panels] - -# PLOT && plot_distribution( -# [body_y_coordinates], -# [results], -# ["VSM"]; -# title="CAD_spanwise_distributions_alpha_$(round(angle_of_attack_deg, digits=1))_delta_$(round(sideslip_deg, digits=1))_yaw_$(round(yaw_rate, digits=1))_v_a_$(round(wind_speed, digits=1))", -# data_type=".pdf", -# is_save=false, -# is_show=true, -# use_tex=USE_TEX -# ) +# Plotting spanwise distributions +body_y_coordinates = [panel.aero_center[2] for panel in body_aero.panels] +PLOT && plot_distribution( + [body_y_coordinates], + [results], + ["VSM"]; + title="pyramid_spanwise_distributions_alpha_$(round(angle_of_attack_deg, digits=1))_delta_$(round(sideslip_deg, digits=1))_yaw_$(round(yaw_rate, digits=1))_v_a_$(round(wind_speed, digits=1))", + data_type=".pdf", + is_save=false, + is_show=true, + use_tex=USE_TEX +) nothing \ No newline at end of file From 8da0fde3e77c20a5d73ff6d68c6d95bcc04e43ca Mon Sep 17 00:00:00 2001 From: jellepoland Date: Wed, 6 Aug 2025 08:54:56 +0200 Subject: [PATCH 16/26] #185, #186 added test_yaml_geometry --- test/test_settings.jl | 18 +- test/test_yaml_geometry.jl | 382 +++++++++++++++++++++++++++++++++++++ 2 files changed, 393 insertions(+), 7 deletions(-) create mode 100644 test/test_yaml_geometry.jl diff --git a/test/test_settings.jl b/test/test_settings.jl index 214c333d..c6e75231 100644 --- a/test/test_settings.jl +++ b/test/test_settings.jl @@ -7,12 +7,16 @@ using VortexStepMethod using Test @testset "Test settings.jl" begin - vss = vs("ram_air_kite/vsm_settings_dual.yaml") - @test vss isa VSMSettings - @test vss.solver_settings isa SolverSettings - @test vss.wings isa Vector{WingSettings} - @test length(vss.wings) == 2 - io = IOBuffer(repr(vss)) - @test countlines(io) == 40 # Updated to match new output format + # Change to project root directory for the test + project_root = dirname(@__DIR__) + cd(project_root) do + vss = vs("ram_air_kite/vsm_settings_dual.yaml") + @test vss isa VSMSettings + @test vss.solver_settings isa SolverSettings + @test vss.wings isa Vector{WingSettings} + @test length(vss.wings) == 2 + io = IOBuffer(repr(vss)) + @test countlines(io) == 40 # Updated to match new output format + end end nothing diff --git a/test/test_yaml_geometry.jl b/test/test_yaml_geometry.jl new file mode 100644 index 00000000..f9a49406 --- /dev/null +++ b/test/test_yaml_geometry.jl @@ -0,0 +1,382 @@ +using VortexStepMethod +using VortexStepMethod: load_polar_data, YamlWing +using LinearAlgebra +using Test +using YAML + +@testset "YAML Geometry Tests" begin + # Setup temporary files for testing + test_csv_path = joinpath(tempdir(), "test_polar.csv") + test_yaml_path = joinpath(tempdir(), "test_wing.yaml") + test_polar_dir = joinpath(tempdir(), "polars") + + # Clean up function + function cleanup_test_files() + for file in [test_csv_path, test_yaml_path] + isfile(file) && rm(file) + end + isdir(test_polar_dir) && rm(test_polar_dir; recursive=true) + end + + @testset "load_polar_data Function Tests" begin + @testset "Valid CSV File" begin + # Create a valid CSV file with polar data + csv_content = """alpha,cl,cd,cm +-10.0,0.1,0.02,-0.01 +-5.0,0.5,0.015,-0.005 +0.0,1.0,0.01,0.0 +5.0,1.5,0.015,0.005 +10.0,1.8,0.025,0.01 +15.0,1.6,0.05,0.015""" + write(test_csv_path, csv_content) + + aero_data, aero_model = load_polar_data(test_csv_path) + + @test aero_model == POLAR_VECTORS + @test aero_data isa Tuple{Vector{Float64}, Vector{Float64}, Vector{Float64}, Vector{Float64}} + @test length(aero_data) == 4 # alpha, cl, cd, cm + @test length(aero_data[1]) == 6 # 6 data points + + # Test that alpha is converted to radians + @test aero_data[1] ≈ deg2rad.([-10.0, -5.0, 0.0, 5.0, 10.0, 15.0]) + + # Test coefficient values + @test aero_data[2] ≈ [0.1, 0.5, 1.0, 1.5, 1.8, 1.6] # cl + @test aero_data[3] ≈ [0.02, 0.015, 0.01, 0.015, 0.025, 0.05] # cd + @test aero_data[4] ≈ [-0.01, -0.005, 0.0, 0.005, 0.01, 0.015] # cm + end + + @testset "Different Column Order" begin + # Test with different column ordering + csv_content = """cm,alpha,cd,cl +-0.01,-10.0,0.02,0.1 +-0.005,-5.0,0.015,0.5 +0.0,0.0,0.01,1.0""" + write(test_csv_path, csv_content) + + aero_data, aero_model = load_polar_data(test_csv_path) + + @test aero_model == POLAR_VECTORS + @test aero_data[1] ≈ deg2rad.([-10.0, -5.0, 0.0]) # alpha + @test aero_data[2] ≈ [0.1, 0.5, 1.0] # cl + @test aero_data[3] ≈ [0.02, 0.015, 0.01] # cd + @test aero_data[4] ≈ [-0.01, -0.005, 0.0] # cm + end + + @testset "Case Insensitive Headers" begin + # Test with mixed case headers + csv_content = """ALPHA,CL,CD,CM +0.0,1.0,0.01,0.0 +5.0,1.5,0.015,0.005""" + write(test_csv_path, csv_content) + + aero_data, aero_model = load_polar_data(test_csv_path) + + @test aero_model == POLAR_VECTORS + @test length(aero_data[1]) == 2 + end + + @testset "Missing File" begin + nonexistent_path = joinpath(tempdir(), "nonexistent.csv") + aero_data, aero_model = load_polar_data(nonexistent_path) + + @test aero_model == INVISCID + @test aero_data === nothing + end + + @testset "Empty File Path" begin + aero_data, aero_model = load_polar_data("") + + @test aero_model == INVISCID + @test aero_data === nothing + end + + @testset "Invalid CSV Format" begin + # Missing required columns + csv_content = """alpha,cl +0.0,1.0 +5.0,1.5""" + write(test_csv_path, csv_content) + + aero_data, aero_model = load_polar_data(test_csv_path) + + @test aero_model == INVISCID + @test aero_data === nothing + end + + @testset "Empty CSV File" begin + write(test_csv_path, "") + + aero_data, aero_model = load_polar_data(test_csv_path) + + @test aero_model == INVISCID + @test aero_data === nothing + end + + @testset "Malformed Data" begin + # Invalid numeric data + csv_content = """alpha,cl,cd,cm +invalid,1.0,0.01,0.0 +5.0,1.5,0.015,0.005""" + write(test_csv_path, csv_content) + + aero_data, aero_model = load_polar_data(test_csv_path) + + @test aero_model == INVISCID + @test aero_data === nothing + end + end + + @testset "YamlWing Constructor Tests" begin + # Create polar data directory and files + mkpath(test_polar_dir) + + # Create polar files + polar1_path = joinpath(test_polar_dir, "1.csv") + polar2_path = joinpath(test_polar_dir, "2.csv") + + polar1_content = """alpha,cl,cd,cm +-10.0,0.1,0.02,-0.01 +0.0,1.0,0.01,0.0 +10.0,1.8,0.025,0.01""" + + polar2_content = """alpha,cl,cd,cm +-10.0,0.15,0.025,-0.015 +0.0,1.1,0.012,0.001 +10.0,1.9,0.03,0.012""" + + write(polar1_path, polar1_content) + write(polar2_path, polar2_content) + + @testset "Valid YAML Wing Construction" begin + # Create a valid YAML wing configuration + yaml_content = """ +wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 4.08, 8.05, 2.0, 4.08, 8.05] + - [2, 0.0, -4.08, 8.05, 2.0, -4.08, 8.05] + - [1, 0.0, 0.0, 4.9, 2.0, 0.0, 4.9] + +wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "polars/1.csv"}] + - [2, polars, {csv_file_path: "polars/2.csv"}] +""" + write(test_yaml_path, yaml_content) + + wing = YamlWing(test_yaml_path; n_panels=4, n_groups=2) + + @test wing isa Wing + @test wing.n_panels == 4 + @test wing.n_groups == 2 + @test wing.spanwise_distribution == LINEAR + @test wing.spanwise_direction ≈ [0.0, 1.0, 0.0] + @test length(wing.sections) == 3 + + # Test section coordinates + @test wing.sections[1].LE_point ≈ [0.0, 4.08, 8.05] + @test wing.sections[1].TE_point ≈ [2.0, 4.08, 8.05] + @test wing.sections[2].LE_point ≈ [0.0, -4.08, 8.05] + @test wing.sections[2].TE_point ≈ [2.0, -4.08, 8.05] + @test wing.sections[3].LE_point ≈ [0.0, 0.0, 4.9] + @test wing.sections[3].TE_point ≈ [2.0, 0.0, 4.9] + + # Test that sections have polar data + @test wing.sections[1].aero_model == POLAR_VECTORS + @test wing.sections[2].aero_model == POLAR_VECTORS + @test wing.sections[3].aero_model == POLAR_VECTORS + + # Test polar data is loaded + @test wing.sections[1].aero_data isa Tuple + @test length(wing.sections[1].aero_data) == 4 + @test length(wing.sections[1].aero_data[1]) == 3 # 3 alpha points + end + + @testset "Wing Constructor Parameters" begin + yaml_content = """ +wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] + +wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "polars/1.csv"}] +""" + write(test_yaml_path, yaml_content) + + # Test custom parameters + wing = YamlWing( + test_yaml_path; + n_panels=8, + n_groups=4, + spanwise_distribution=COSINE, + remove_nan=false + ) + + @test wing.n_panels == 8 + @test wing.n_groups == 4 + @test wing.spanwise_distribution == COSINE + @test !wing.remove_nan + end + + @testset "Missing Polar Files" begin + # Create YAML with non-existent polar files + yaml_content = """ +wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + +wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "nonexistent.csv"}] +""" + write(test_yaml_path, yaml_content) + + wing = YamlWing(test_yaml_path; n_panels=2) + + # Should fall back to INVISCID model + @test wing.sections[1].aero_model == INVISCID + @test wing.sections[1].aero_data === nothing + end + + @testset "Sections Without Polar Files" begin + # Create YAML with empty polar file paths + yaml_content = """ +wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + +wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: ""}] +""" + write(test_yaml_path, yaml_content) + + wing = YamlWing(test_yaml_path; n_panels=2) + + # Should fall back to INVISCID model + @test wing.sections[1].aero_model == INVISCID + end + + @testset "Invalid Parameters" begin + yaml_content = """ +wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + +wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "polars/1.csv"}] +""" + write(test_yaml_path, yaml_content) + + # Test invalid n_panels/n_groups combination + @test_throws ArgumentError YamlWing(test_yaml_path; n_panels=5, n_groups=2) + + # Test invalid spanwise direction + @test_throws ArgumentError YamlWing(test_yaml_path; spanwise_direction=[1.0, 0.0, 0.0]) + end + + @testset "Relative Path Resolution" begin + # Test that relative paths in CSV files are resolved relative to YAML file + subdir = joinpath(tempdir(), "subtest") + mkpath(subdir) + subdir_polar_dir = joinpath(subdir, "polars") + mkpath(subdir_polar_dir) + + # Create polar file in subdirectory + subdir_polar_path = joinpath(subdir_polar_dir, "airfoil.csv") + write(subdir_polar_path, polar1_content) + + # Create YAML in subdirectory with relative path + subdir_yaml_path = joinpath(subdir, "wing.yaml") + yaml_content = """ +wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + +wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "polars/airfoil.csv"}] +""" + write(subdir_yaml_path, yaml_content) + + wing = YamlWing(subdir_yaml_path; n_panels=2) + + # Should successfully load polar data with relative path + @test wing.sections[1].aero_model == POLAR_VECTORS + @test wing.sections[1].aero_data isa Tuple + + # Cleanup + rm(subdir; recursive=true) + end + + @testset "Complex Wing Geometry" begin + # Test with more complex wing geometry + yaml_content = """ +wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 5.0, 0.0, 2.0, 5.0, 0.5] + - [2, 0.2, 3.0, 0.2, 1.8, 3.0, 0.3] + - [2, 0.4, 1.0, 0.4, 1.6, 1.0, 0.1] + - [1, 0.5, 0.0, 0.5, 1.5, 0.0, 0.0] + - [2, 0.4, -1.0, 0.4, 1.6, -1.0, 0.1] + - [2, 0.2, -3.0, 0.2, 1.8, -3.0, 0.3] + - [1, 0.0, -5.0, 0.0, 2.0, -5.0, 0.5] + +wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "polars/1.csv"}] + - [2, polars, {csv_file_path: "polars/2.csv"}] +""" + write(test_yaml_path, yaml_content) + + wing = YamlWing(test_yaml_path; n_panels=12, n_groups=3) + + @test wing.n_panels == 12 + @test wing.n_groups == 3 + @test length(wing.sections) == 7 + + # Test that different airfoil_ids get different polar data + @test wing.sections[1].aero_model == POLAR_VECTORS + @test wing.sections[2].aero_model == POLAR_VECTORS + + # Verify geometric progression along wingspan + @test wing.sections[1].LE_point[2] == 5.0 # First section at y=5 + @test wing.sections[4].LE_point[2] == 0.0 # Middle section at y=0 + @test wing.sections[7].LE_point[2] == -5.0 # Last section at y=-5 + end + end + + # Cleanup after all tests + cleanup_test_files() +end From bcb06ffb437d943bfae4d12a46d8a94c3dbe480c Mon Sep 17 00:00:00 2001 From: jellepoland Date: Thu, 7 Aug 2025 11:12:04 +0200 Subject: [PATCH 17/26] #186 working on test folder --- .../1.csv | 0 .../10.csv | 0 .../11.csv | 0 .../12.csv | 0 .../13.csv | 0 .../14.csv | 0 .../15.csv | 0 .../16.csv | 0 .../17.csv | 0 .../18.csv | 0 .../19.csv | 0 .../2.csv | 0 .../3.csv | 0 .../4.csv | 0 .../5.csv | 0 .../6.csv | 0 .../7.csv | 0 .../8.csv | 0 .../9.csv | 0 data/TUDELFT_V3_KITE/vsm_settings.yaml | 2 +- ...ted.yaml => wing_geometry_polars_CFD.yaml} | 41 +-- examples/V3_kite.jl | 47 +-- examples/pyramid_model.jl | 44 +-- src/VortexStepMethod.jl | 4 +- src/body_aerodynamics.jl | 41 +++ src/settings.jl | 12 +- src/solver.jl | 11 + src/yaml_geometry.jl | 38 ++- test/README.md | 104 +++++++ .../VortexStepMethod/test_VortexStepMethod.jl | 0 test/body_aerodynamics/complete_settings.yaml | 18 ++ test/body_aerodynamics/simple_polar.csv | 4 + .../test_body_aerodynamics.jl | 40 ++- test/{ => body_aerodynamics}/test_results.jl | 2 +- test/body_aerodynamics/test_wing.yaml | 12 + test/{ => filament}/test_bound_filament.jl | 0 .../test_semi_infinite_filament.jl | 40 +-- test/{ => panel}/test_panel.jl | 2 +- test/{ => plotting}/test_plotting.jl | 0 test/{aqua.jl => polars/test_polars.jl} | 0 test/{ => ram_geometry}/test_kite_geometry.jl | 0 test/runtests.jl | 26 +- test/settings/basic_llt.yaml | 9 + test/settings/basic_vsm.yaml | 9 + test/{ => settings}/test_settings.jl | 4 +- test/solver/solver_settings.yaml | 18 ++ test/solver/solver_test_polar.csv | 4 + test/solver/solver_test_wing.yaml | 12 + test/solver/test_solver.jl | 34 +++ test/test_data_utils.jl | 134 +++++++++ test/wake/test_wake.jl | 0 .../{ => wing_geometry}/test_wing_geometry.jl | 0 test/yaml_geometry/alternate_airfoil.csv | 7 + test/yaml_geometry/complex_wing.yaml | 18 ++ test/yaml_geometry/simple_wing.yaml | 12 + test/yaml_geometry/standard_airfoil.csv | 7 + .../{ => yaml_geometry}/test_yaml_geometry.jl | 276 ++++++++++++------ 57 files changed, 804 insertions(+), 228 deletions(-) rename data/TUDELFT_V3_KITE/{2D_polars_CFD_re5e5_pchip_fitted => polars_CFD}/1.csv (100%) rename data/TUDELFT_V3_KITE/{2D_polars_CFD_re5e5_pchip_fitted => polars_CFD}/10.csv (100%) rename data/TUDELFT_V3_KITE/{2D_polars_CFD_re5e5_pchip_fitted => polars_CFD}/11.csv (100%) rename 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data/TUDELFT_V3_KITE/{2D_polars_CFD_re5e5_pchip_fitted => polars_CFD}/5.csv (100%) rename data/TUDELFT_V3_KITE/{2D_polars_CFD_re5e5_pchip_fitted => polars_CFD}/6.csv (100%) rename data/TUDELFT_V3_KITE/{2D_polars_CFD_re5e5_pchip_fitted => polars_CFD}/7.csv (100%) rename data/TUDELFT_V3_KITE/{2D_polars_CFD_re5e5_pchip_fitted => polars_CFD}/8.csv (100%) rename data/TUDELFT_V3_KITE/{2D_polars_CFD_re5e5_pchip_fitted => polars_CFD}/9.csv (100%) rename data/TUDELFT_V3_KITE/{wing_geometry_CAD_CFD_polars_pchip_fitted.yaml => wing_geometry_polars_CFD.yaml} (88%) create mode 100644 test/README.md create mode 100644 test/VortexStepMethod/test_VortexStepMethod.jl create mode 100644 test/body_aerodynamics/complete_settings.yaml create mode 100644 test/body_aerodynamics/simple_polar.csv rename test/{ => body_aerodynamics}/test_body_aerodynamics.jl (92%) rename test/{ => body_aerodynamics}/test_results.jl (99%) create mode 100644 test/body_aerodynamics/test_wing.yaml rename test/{ => 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a/data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/2.csv b/data/TUDELFT_V3_KITE/polars_CFD/2.csv similarity index 100% rename from data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/2.csv rename to data/TUDELFT_V3_KITE/polars_CFD/2.csv diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/3.csv b/data/TUDELFT_V3_KITE/polars_CFD/3.csv similarity index 100% rename from data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/3.csv rename to data/TUDELFT_V3_KITE/polars_CFD/3.csv diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/4.csv b/data/TUDELFT_V3_KITE/polars_CFD/4.csv similarity index 100% rename from data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/4.csv rename to data/TUDELFT_V3_KITE/polars_CFD/4.csv diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/5.csv b/data/TUDELFT_V3_KITE/polars_CFD/5.csv similarity index 100% rename from data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/5.csv rename to data/TUDELFT_V3_KITE/polars_CFD/5.csv diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/6.csv b/data/TUDELFT_V3_KITE/polars_CFD/6.csv similarity index 100% rename from data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/6.csv rename to data/TUDELFT_V3_KITE/polars_CFD/6.csv diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/7.csv b/data/TUDELFT_V3_KITE/polars_CFD/7.csv similarity index 100% rename from data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/7.csv rename to data/TUDELFT_V3_KITE/polars_CFD/7.csv diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/8.csv b/data/TUDELFT_V3_KITE/polars_CFD/8.csv similarity index 100% rename from data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/8.csv rename to data/TUDELFT_V3_KITE/polars_CFD/8.csv diff --git a/data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/9.csv b/data/TUDELFT_V3_KITE/polars_CFD/9.csv similarity index 100% rename from data/TUDELFT_V3_KITE/2D_polars_CFD_re5e5_pchip_fitted/9.csv rename to data/TUDELFT_V3_KITE/polars_CFD/9.csv diff --git a/data/TUDELFT_V3_KITE/vsm_settings.yaml b/data/TUDELFT_V3_KITE/vsm_settings.yaml index 6ee01847..4e6fda6d 100644 --- a/data/TUDELFT_V3_KITE/vsm_settings.yaml +++ b/data/TUDELFT_V3_KITE/vsm_settings.yaml @@ -44,7 +44,7 @@ condition: # Define wing geometry files and discretization parameters wings: - name: V3_Kite # Wing identifier for output labeling - geometry_file: data/TUDELFT_V3_KITE/wing_geometry_CAD_CFD_polars_pchip_fitted.yaml + geometry_file: data/TUDELFT_V3_KITE/wing_geometry_polars_CFD.yaml n_panels: 36 # Total number of panels along wingspan n_groups: 1 # Number of panel groups (must divide n_panels) spanwise_panel_distribution: LINEAR # Panel spacing algorithm diff --git a/data/TUDELFT_V3_KITE/wing_geometry_CAD_CFD_polars_pchip_fitted.yaml b/data/TUDELFT_V3_KITE/wing_geometry_polars_CFD.yaml similarity index 88% rename from data/TUDELFT_V3_KITE/wing_geometry_CAD_CFD_polars_pchip_fitted.yaml rename to data/TUDELFT_V3_KITE/wing_geometry_polars_CFD.yaml index a8e2612f..fb1313c8 100644 --- a/data/TUDELFT_V3_KITE/wing_geometry_CAD_CFD_polars_pchip_fitted.yaml +++ b/data/TUDELFT_V3_KITE/wing_geometry_polars_CFD.yaml @@ -83,25 +83,28 @@ wing_airfoils: reynolds: !!float 1e6 # Reynolds number headers: [airfoil_id, type, info_dict] data: - - [1, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/1.csv"}] - - [2, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/2.csv"}] - - [3, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/3.csv"}] - - [4, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/4.csv"}] - - [5, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/5.csv"}] - - [6, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/6.csv"}] - - [7, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/7.csv"}] - - [8, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/8.csv"}] - - [9, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/9.csv"}] - - [10, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/10.csv"}] - - [11, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/11.csv"}] - - [12, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/12.csv"}] - - [13, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/13.csv"}] - - [14, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/14.csv"}] - - [15, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/15.csv"}] - - [16, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/16.csv"}] - - [17, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/17.csv"}] - - [18, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/18.csv"}] - - [19, polars, {csv_file_path: "2D_polars_CFD_re5e5_pchip_fitted/19.csv"}] + # The polars were generated using 2D RANS CFD simulations at Re=5e5 + # And fitted using PCHIP interpolation + # See --> https://repository.tudelft.nl/record/uuid:865d59fc-ccff-462e-9bac-e81725f1c0c9 + - [1, polars, {csv_file_path: "polars_CFD/1.csv"}] + - [2, polars, {csv_file_path: "polars_CFD/2.csv"}] + - [3, polars, {csv_file_path: "polars_CFD/3.csv"}] + - [4, polars, {csv_file_path: "polars_CFD/4.csv"}] + - [5, polars, {csv_file_path: "polars_CFD/5.csv"}] + - [6, polars, {csv_file_path: "polars_CFD/6.csv"}] + - [7, polars, {csv_file_path: "polars_CFD/7.csv"}] + - [8, polars, {csv_file_path: "polars_CFD/8.csv"}] + - [9, polars, {csv_file_path: "polars_CFD/9.csv"}] + - [10, polars, {csv_file_path: "polars_CFD/10.csv"}] + - [11, polars, {csv_file_path: "polars_CFD/11.csv"}] + - [12, polars, {csv_file_path: "polars_CFD/12.csv"}] + - [13, polars, {csv_file_path: "polars_CFD/13.csv"}] + - [14, polars, {csv_file_path: "polars_CFD/14.csv"}] + - [15, polars, {csv_file_path: "polars_CFD/15.csv"}] + - [16, polars, {csv_file_path: "polars_CFD/16.csv"}] + - [17, polars, {csv_file_path: "polars_CFD/17.csv"}] + - [18, polars, {csv_file_path: "polars_CFD/18.csv"}] + - [19, polars, {csv_file_path: "polars_CFD/19.csv"}] diff --git a/examples/V3_kite.jl b/examples/V3_kite.jl index 85154a95..9f50b6d4 100644 --- a/examples/V3_kite.jl +++ b/examples/V3_kite.jl @@ -2,17 +2,7 @@ using LinearAlgebra using VortexStepMethod using ControlPlots -project_dir = dirname(dirname(pathof(VortexStepMethod))) # Go up one level from src to project root - -# Load VSM settings from YAML configuration file -settings = vs("TUDELFT_V3_KITE/vsm_settings.yaml") - -# Extract flight conditions from settings -wind_speed = settings.condition.wind_speed -angle_of_attack_deg = settings.condition.alpha -sideslip_deg = settings.condition.beta -yaw_rate = settings.condition.yaw_rate - +project_dir = dirname(dirname(pathof(VortexStepMethod))) # Go up one level from src to project root# literature_paths = [ joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv"), joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv"), @@ -28,36 +18,21 @@ labels= [ ] # Load VSM settings from YAML configuration file -settings = vs("TUDELFT_V3_KITE/vsm_settings.yaml") +settings = VSMSettings("TUDELFT_V3_KITE/vsm_settings.yaml") # Create wing, body_aero, and solver objects using settings -wing = YamlWing(settings.wings[1].geometry_file; - n_panels=settings.wings[1].n_panels, - n_groups=settings.wings[1].n_groups, - spanwise_distribution=settings.wings[1].spanwise_panel_distribution -) +wing = Wing(settings) body_aero = BodyAerodynamics([wing]) -solver = Solver(body_aero; - aerodynamic_model_type=settings.solver_settings.aerodynamic_model_type, - density=settings.solver_settings.density, - max_iterations=settings.solver_settings.max_iterations, - rtol=settings.solver_settings.rtol, - relaxation_factor=settings.solver_settings.relaxation_factor, - core_radius_fraction=settings.solver_settings.core_radius_fraction, -) -# Set flight conditions -α = deg2rad(settings.condition.alpha) -β = deg2rad(settings.condition.beta) -va = settings.condition.wind_speed * [ - cos(α)*cos(β), # X_b (forward) - sin(β), # Y_b (right) - sin(α)*cos(β) # Z_b (down) -] -set_va!(body_aero, va) -# Run the solver -results = VortexStepMethod.solve(solver, body_aero; log=true) +solver = Solver(body_aero, settings) +# Set flight conditions from settings +set_va!(body_aero, settings) +# Extract values for plotting (optional - for reference) +wind_speed = settings.condition.wind_speed +angle_of_attack_deg = settings.condition.alpha +sideslip_deg = settings.condition.beta +yaw_rate = settings.condition.yaw_rate # Using plotting modules, to create more comprehensive plots PLOT = true diff --git a/examples/pyramid_model.jl b/examples/pyramid_model.jl index 45e72b86..837e26ef 100644 --- a/examples/pyramid_model.jl +++ b/examples/pyramid_model.jl @@ -4,40 +4,22 @@ using ControlPlots project_dir = dirname(dirname(pathof(VortexStepMethod))) # Go up one level from src to project root -# Load VSM settings from YAML configuration file -settings = vs("pyramid_model/vsm_settings.yaml") +# Load VSM vsm_settings from YAML configuration file +vsm_settings = VSMSettings("pyramid_model/vsm_settings.yaml") -# Extract flight conditions from settings -wind_speed = settings.condition.wind_speed -angle_of_attack_deg = settings.condition.alpha -sideslip_deg = settings.condition.beta -yaw_rate = settings.condition.yaw_rate - -# Create wing, body_aero, and solver objects using settings -wing = YamlWing(settings.wings[1].geometry_file; - n_panels=settings.wings[1].n_panels, - n_groups=settings.wings[1].n_groups, - spanwise_distribution=settings.wings[1].spanwise_panel_distribution -) +# Create wing, body_aero, and solver objects using vsm_settings +wing = Wing(vsm_settings) body_aero = BodyAerodynamics([wing]) -solver = Solver(body_aero; - aerodynamic_model_type=settings.solver_settings.aerodynamic_model_type, - density=settings.solver_settings.density, - max_iterations=settings.solver_settings.max_iterations, - rtol=settings.solver_settings.rtol, - relaxation_factor=settings.solver_settings.relaxation_factor, - core_radius_fraction=settings.solver_settings.core_radius_fraction, -) +solver = Solver(body_aero, vsm_settings) + +# Set flight conditions from settings +set_va!(body_aero, vsm_settings) -# Set flight conditions -α = deg2rad(settings.condition.alpha) -β = deg2rad(settings.condition.beta) -va = settings.condition.wind_speed * [ - cos(α)*cos(β), # X_b (forward) - sin(β), # Y_b (right) - sin(α)*cos(β) # Z_b (down) -] -set_va!(body_aero, va) +# Extract values for plotting (optional - for reference) +wind_speed = vsm_settings.condition.wind_speed +angle_of_attack_deg = vsm_settings.condition.alpha +sideslip_deg = vsm_settings.condition.beta +yaw_rate = vsm_settings.condition.yaw_rate # Run the solver results = VortexStepMethod.solve(solver, body_aero; log=true) diff --git a/src/VortexStepMethod.jl b/src/VortexStepMethod.jl index ffb7ae6c..5d8b1918 100644 --- a/src/VortexStepMethod.jl +++ b/src/VortexStepMethod.jl @@ -26,8 +26,8 @@ using StructMapping using Xfoil # Export public interface -export VSMSettings, WingSettings, SolverSettings, vs -export Wing, Section, RamAirWing, YamlWing, reinit! +export VSMSettings, WingSettings, SolverSettings +export Wing, Section, RamAirWing, reinit! export BodyAerodynamics export Solver, solve, solve_base!, solve!, VSMSolution, linearize export calculate_results diff --git a/src/body_aerodynamics.jl b/src/body_aerodynamics.jl index ef0509c8..87e75fec 100644 --- a/src/body_aerodynamics.jl +++ b/src/body_aerodynamics.jl @@ -667,3 +667,44 @@ function set_va!(body_aero::BodyAerodynamics, va_distribution::Vector{VelVector} return nothing end +""" + set_va!(body_aero::BodyAerodynamics, settings::VSMSettings) + +Set velocity array from VSM settings configuration. + +This convenience method extracts flight conditions from VSMSettings and +constructs the velocity vector in the body reference frame based on: +- Wind speed from settings.condition.wind_speed +- Angle of attack from settings.condition.alpha (converted from degrees) +- Sideslip angle from settings.condition.beta (converted from degrees) + +The velocity vector is constructed as: +- X_b (forward): wind_speed * cos(α) * cos(β) +- Y_b (right): wind_speed * sin(β) +- Z_b (down): wind_speed * sin(α) * cos(β) + +# Arguments +- `body_aero::BodyAerodynamics`: The aerodynamic body to modify +- `settings::VSMSettings`: Settings object containing flight conditions + +# Example +```julia +settings = VSMSettings("path/to/settings.yaml") +body_aero = BodyAerodynamics([wing]) +set_va!(body_aero, settings) +``` +""" +function set_va!(body_aero::BodyAerodynamics, settings::VSMSettings) + α = deg2rad(settings.condition.alpha) + β = deg2rad(settings.condition.beta) + wind_speed = settings.condition.wind_speed + + va = wind_speed * [ + cos(α)*cos(β), # X_b (forward) + sin(β), # Y_b (right) + sin(α)*cos(β) # Z_b (down) + ] + + set_va!(body_aero, va) +end + diff --git a/src/settings.jl b/src/settings.jl index 80ffeaa1..fe538ed9 100644 --- a/src/settings.jl +++ b/src/settings.jl @@ -40,7 +40,7 @@ end solver_settings::SolverSettings = SolverSettings() end -function vs(filename) +function VSMSettings(filename) # Uwe's suggested 3-line approach using StructMapping.jl (adapted) data = YAML.load_file(joinpath("data", filename)) @@ -100,14 +100,14 @@ function vs(filename) return vsm_settings end -function Base.show(io::IO, vs::VSMSettings) +function Base.show(io::IO, vsm_settings::VSMSettings) println(io, "VSMSettings:") - print(io, replace(repr(vs.condition), "\n" => "\n ")) - for (i, wing) in pairs(vs.wings) + print(io, replace(repr(vsm_settings.condition), "\n" => "\n ")) + for (i, wing) in pairs(vsm_settings.wings) if i==1 print(io, " ") end print(io, replace(repr(wing), "\n" => "\n ")) end - print(io, replace(repr(vs.solver_settings), "\n" => "\n ")) -end + print(io, replace(repr(vsm_settings.solver_settings), "\n" => "\n ")) +end \ No newline at end of file diff --git a/src/solver.jl b/src/solver.jl index 3247e669..f3ea1085 100644 --- a/src/solver.jl +++ b/src/solver.jl @@ -137,6 +137,17 @@ function Solver(body_aero; kwargs...) return Solver{P,G}(; kwargs...) end +function Solver(body_aero, settings::VSMSettings) + Solver(body_aero; + aerodynamic_model_type=settings.solver_settings.aerodynamic_model_type, + density=settings.solver_settings.density, + max_iterations=settings.solver_settings.max_iterations, + rtol=settings.solver_settings.rtol, + relaxation_factor=settings.solver_settings.relaxation_factor, + core_radius_fraction=settings.solver_settings.core_radius_fraction, + ) +end + """ solve!(solver::Solver, body_aero::BodyAerodynamics, gamma_distribution=solver.sol.gamma_distribution; log=false, reference_point=zeros(MVec3), moment_frac=0.1) diff --git a/src/yaml_geometry.jl b/src/yaml_geometry.jl index c6d77494..6f395014 100644 --- a/src/yaml_geometry.jl +++ b/src/yaml_geometry.jl @@ -100,7 +100,7 @@ end """ - YamlWing(geometry_file; kwargs...) + Wing(geometry_file; kwargs...) Create a wing model from YAML configuration file with CSV polar data. @@ -144,15 +144,15 @@ wing_airfoils: # Example ```julia # Create a YAML-based wing from configuration file -wing = YamlWing( +wing = Wing( "path/to/wing_config.yaml"; n_panels=40, n_groups=4 ) ``` """ -function YamlWing( - geometry_file; +function Wing( + geometry_file::String; n_panels=20, n_groups=1, spanwise_distribution=LINEAR, @@ -237,3 +237,33 @@ function YamlWing( return wing end + +""" + Wing(settings::VSMSettings) + +Create a wing model from VSM settings configuration. + +This constructor is a convenience wrapper that extracts wing configuration +from VSMSettings and creates a Wing using the YAML geometry file path and +parameters specified in the settings. + +# Arguments +- `settings`: VSMSettings object containing wing configuration + +# Returns +A fully initialized `Wing` instance ready for aerodynamic simulation. + +# Example +```julia +# Load settings and create wing in one step +settings = VSMSettings("path/to/vsm_settings.yaml") +wing = Wing(settings) +``` +""" +function Wing(settings::VSMSettings) + Wing(settings.wings[1].geometry_file; + n_panels=settings.wings[1].n_panels, + n_groups=settings.wings[1].n_groups, + spanwise_distribution=settings.wings[1].spanwise_panel_distribution + ) +end diff --git a/test/README.md b/test/README.md new file mode 100644 index 00000000..2c7c7cba --- /dev/null +++ b/test/README.md @@ -0,0 +1,104 @@ +# Test Data Organization + +This directory contains organized test data for the VortexStepMethod.jl test suite. + +## Structure + +The test data is organized by source module being tested, following the structure of the `src/` directory: + +``` +test/data/ +├── body_aerodynamics/ # Tests for src/body_aerodynamics.jl +│ ├── wings/ +│ │ └── test_wing.yaml +│ ├── polars/ +│ │ └── simple_polar.csv +│ └── complete_settings.yaml +├── yaml_geometry/ # Tests for src/yaml_geometry.jl +│ ├── wings/ +│ │ ├── simple_wing.yaml +│ │ └── complex_wing.yaml +│ └── polars/ +│ ├── standard_airfoil.csv +│ └── alternate_airfoil.csv +├── solver/ # Tests for src/solver.jl +│ ├── wings/ +│ │ └── solver_test_wing.yaml +│ ├── polars/ +│ │ └── solver_test_polar.csv +│ └── solver_settings.yaml +├── settings/ # Common settings files +│ ├── basic_vsm.yaml +│ └── basic_llt.yaml +└── wing_geometry/ # Tests for src/wing_geometry.jl (future) +``` + +## Usage + +Use the helper functions in `test_data_utils.jl` to access test data: + +### Basic Path Access +```julia +include("test_data_utils.jl") + +# Get paths to test data files +wing_file = test_data_path("yaml_geometry", "wings", "simple_wing.yaml") +polar_file = test_data_path("yaml_geometry", "polars", "standard_airfoil.csv") +settings_file = test_data_path("settings", "basic_vsm.yaml") +``` + +### Module-Specific Convenience Functions +```julia +# Get standard wing file for a module +wing_file = get_standard_wing_file("body_aerodynamics") + +# Get complete settings file for a module +settings_file = get_complete_settings_file("solver") + +# Create temporary settings with custom parameters +temp_settings = create_temp_wing_settings("yaml_geometry", "simple_wing.yaml"; + alpha=15.0, wind_speed=25.0) +``` + +## Design Principles + +1. **Module Isolation**: Each source module has its own test data directory +2. **Consistent Structure**: All modules follow the same subdirectory pattern (wings/, polars/, etc.) +3. **Reusable Components**: Common files (like basic settings) are shared in the `settings/` directory +4. **Clear Naming**: File names clearly indicate their purpose and content +5. **Self-Contained**: Each module's data is independent and can be used in isolation + +## Adding New Test Data + +When adding test data for a new source module: + +1. Create a new directory under `test/data/` matching the source file name +2. Add subdirectories as needed (`wings/`, `polars/`, etc.) +3. Update `test_data_utils.jl` to include helper functions for the new module +4. Follow the existing naming conventions + +## File Descriptions + +### Wing Geometry Files (.yaml) +- `simple_wing.yaml`: Basic 2-section wing for common tests +- `complex_wing.yaml`: Multi-section wing with multiple airfoil types +- `test_wing.yaml`: Simple wing for body aerodynamics tests +- `solver_test_wing.yaml`: Wing optimized for solver testing + +### Polar Data Files (.csv) +- `standard_airfoil.csv`: Standard 6-point polar data +- `alternate_airfoil.csv`: Alternative airfoil with different coefficients +- `simple_polar.csv`: Minimal 3-point polar for basic tests +- `solver_test_polar.csv`: Polar data for solver tests + +### Settings Files (.yaml) +- `basic_vsm.yaml`: Basic VSM solver settings +- `basic_llt.yaml`: Basic LLT solver settings +- `complete_settings.yaml`: Full wing + solver configuration +- `solver_settings.yaml`: Solver-specific configuration + +This organization makes it easy to: +- Find test data relevant to specific source modules +- Avoid conflicts between different test requirements +- Maintain and update test data independently +- Add new test cases without affecting existing ones diff --git a/test/VortexStepMethod/test_VortexStepMethod.jl b/test/VortexStepMethod/test_VortexStepMethod.jl new file mode 100644 index 00000000..e69de29b diff --git a/test/body_aerodynamics/complete_settings.yaml b/test/body_aerodynamics/complete_settings.yaml new file mode 100644 index 00000000..a40ff608 --- /dev/null +++ b/test/body_aerodynamics/complete_settings.yaml @@ -0,0 +1,18 @@ +wings: + - name: "body_aero_test_wing" + geometry_file: "test/body_aerodynamics/test_wing.yaml" + n_panels: 4 + n_groups: 2 + spanwise_panel_distribution: COSINE + spanwise_direction: [0.0, 1.0, 0.0] + remove_nan: true + +solver_settings: + aerodynamic_model_type: VSM + density: 1.225 + type_initial_gamma_distribution: ZEROS + +condition: + alpha: 10.0 + beta: 5.0 + wind_speed: 15.0 diff --git a/test/body_aerodynamics/simple_polar.csv b/test/body_aerodynamics/simple_polar.csv new file mode 100644 index 00000000..7e043d9c --- /dev/null +++ b/test/body_aerodynamics/simple_polar.csv @@ -0,0 +1,4 @@ +alpha,cl,cd,cm +-10.0,0.1,0.02,-0.01 +0.0,1.0,0.01,0.0 +10.0,1.8,0.025,0.01 diff --git a/test/test_body_aerodynamics.jl b/test/body_aerodynamics/test_body_aerodynamics.jl similarity index 92% rename from test/test_body_aerodynamics.jl rename to test/body_aerodynamics/test_body_aerodynamics.jl index 63154fff..c38dd8be 100644 --- a/test/test_body_aerodynamics.jl +++ b/test/body_aerodynamics/test_body_aerodynamics.jl @@ -4,7 +4,8 @@ using LinearAlgebra using Test using Logging -include("utils.jl") +include("../utils.jl") +include("../test_data_utils.jl") @testset "Induction Matrix Creation" begin # Setup @@ -413,3 +414,40 @@ end @test length(results_NEW["cd_distribution"]) == length(body_aero.panels) end +@testset "set_va! with VSMSettings" begin + # Use module-specific test data files + wing_file = test_data_path("body_aerodynamics", "test_wing.yaml") + settings_file = create_temp_wing_settings("body_aerodynamics", "test_wing.yaml"; alpha=10.0, beta=5.0, wind_speed=15.0) + + try + # Test set_va! with VSMSettings + settings = VSMSettings(settings_file) + wing = Wing(settings) + body_aero = BodyAerodynamics([wing]) + + # Set velocity using convenience method + set_va!(body_aero, settings) + + # Calculate expected velocity vector + α = deg2rad(10.0) + β = deg2rad(5.0) + wind_speed = 15.0 + expected_va = wind_speed * [ + cos(α)*cos(β), # X_b (forward) + sin(β), # Y_b (right) + sin(α)*cos(β) # Z_b (down) + ] + + # Verify that all panels have the correct velocity + for panel in body_aero.panels + @test panel.va ≈ expected_va atol=1e-10 + end + + # Verify body_aero._va is set correctly + @test body_aero._va ≈ expected_va atol=1e-10 + + finally + # Cleanup + rm(settings_file; force=true) + end +end \ No newline at end of file diff --git a/test/test_results.jl b/test/body_aerodynamics/test_results.jl similarity index 99% rename from test/test_results.jl rename to test/body_aerodynamics/test_results.jl index 762b6d17..c9436043 100644 --- a/test/test_results.jl +++ b/test/body_aerodynamics/test_results.jl @@ -6,7 +6,7 @@ using Logging if !@isdefined ram_wing # Use absolute paths to ensure files are found - data_dir = joinpath(dirname(@__DIR__), "data", "ram_air_kite") + data_dir = joinpath(dirname(dirname(@__DIR__)), "data", "ram_air_kite") body_path = joinpath(tempdir(), "ram_air_kite_body.obj") foil_path = joinpath(tempdir(), "ram_air_kite_foil.dat") diff --git a/test/body_aerodynamics/test_wing.yaml b/test/body_aerodynamics/test_wing.yaml new file mode 100644 index 00000000..964fe9ec --- /dev/null +++ b/test/body_aerodynamics/test_wing.yaml @@ -0,0 +1,12 @@ +wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] + +wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "simple_polar.csv"}] diff --git a/test/test_bound_filament.jl b/test/filament/test_bound_filament.jl similarity index 100% rename from test/test_bound_filament.jl rename to test/filament/test_bound_filament.jl diff --git a/test/test_semi_infinite_filament.jl b/test/filament/test_semi_infinite_filament.jl similarity index 87% rename from test/test_semi_infinite_filament.jl rename to test/filament/test_semi_infinite_filament.jl index e21ec1cd..76e324cb 100644 --- a/test/test_semi_infinite_filament.jl +++ b/test/filament/test_semi_infinite_filament.jl @@ -1,7 +1,7 @@ -using VortexStepMethod: SemiInfiniteFilament, velocity_3D_trailing_vortex_semiinfinite! +using VortexStepMethod: SemiInfiniteFilament, velocity_3D_trailing_vortex_semiinfinite!, reinit! using LinearAlgebra using Test -using BenchmarkTools +# using BenchmarkTools function create_test_filament2() x1 = [0.0, 0.0, 0.0] @@ -42,24 +42,24 @@ end core_radius_fraction = 0.01 work_vectors = ntuple(_ -> Vector{Float64}(undef, 3), 10) - @testset "Allocation Tests" begin - filament = create_test_filament2() - control_point = [0.5, 0.5, 2.0] - induced_velocity = zeros(3) - - b = @benchmarkable velocity_3D_trailing_vortex_semiinfinite!( - $induced_velocity, - $filament, - $filament.direction, - $control_point, - $gamma, - $filament.vel_mag, - $work_vectors - ) - result = run(b) - @test result.allocs == 0 - @test result.memory == 0 - end + # @testset "Allocation Tests" begin + # filament = create_test_filament2() + # control_point = [0.5, 0.5, 2.0] + # induced_velocity = zeros(3) + # + # b = @benchmarkable velocity_3D_trailing_vortex_semiinfinite!( + # $induced_velocity, + # $filament, + # $filament.direction, + # $control_point, + # $gamma, + # $filament.vel_mag, + # $work_vectors + # ) + # result = run(b) + # @test result.allocs == 0 + # @test result.memory == 0 + # end @testset "Calculate Induced Velocity" begin filament = create_test_filament2() diff --git a/test/test_panel.jl b/test/panel/test_panel.jl similarity index 99% rename from test/test_panel.jl rename to test/panel/test_panel.jl index ff4a89ba..8048c548 100644 --- a/test/test_panel.jl +++ b/test/panel/test_panel.jl @@ -2,7 +2,7 @@ using VortexStepMethod: Panel, Section, calculate_relative_alpha_and_relative_ve using Interpolations: linear_interpolation, Line using LinearAlgebra using Test -using BenchmarkTools +# using BenchmarkTools function create_panel(section1::Section, section2::Section) # Calculate panel geometry diff --git a/test/test_plotting.jl b/test/plotting/test_plotting.jl similarity index 100% rename from test/test_plotting.jl rename to test/plotting/test_plotting.jl diff --git a/test/aqua.jl b/test/polars/test_polars.jl similarity index 100% rename from test/aqua.jl rename to test/polars/test_polars.jl diff --git a/test/test_kite_geometry.jl b/test/ram_geometry/test_kite_geometry.jl similarity index 100% rename from test/test_kite_geometry.jl rename to test/ram_geometry/test_kite_geometry.jl diff --git a/test/runtests.jl b/test/runtests.jl index 7f2b359f..c1155d20 100644 --- a/test/runtests.jl +++ b/test/runtests.jl @@ -23,14 +23,20 @@ println("Running tests...") if build_is_production_build include("bench.jl") end - include("test_settings.jl") - include("test_bound_filament.jl") - include("test_panel.jl") - include("test_semi_infinite_filament.jl") - include("test_body_aerodynamics.jl") - include("test_results.jl") - include("test_kite_geometry.jl") - include("test_wing_geometry.jl") - include("test_plotting.jl") - include("aqua.jl") + include("body_aerodynamics/test_body_aerodynamics.jl") + include("body_aerodynamics/test_results.jl") + include("filament/test_bound_filament.jl") + include("filament/test_semi_infinite_filament.jl") + include("panel/test_panel.jl") + include("plotting/test_plotting.jl") + include("polars/test_polars.jl") + include("ram_geometry/test_kite_geometry.jl") + include("settings/test_settings.jl") + include("solver/test_solver.jl") + include("solver/test_solver_results.jl") + include("wing_geometry/test_wing_settings.jl") + include("VortexStepMethod/test_vortex_step_method.jl") + include("wake/test_wake.jl") + include("wing_geometry/test_wing_geometry.jl") + include("yaml_geometry/test_yaml_geometry.jl") end \ No newline at end of file diff --git a/test/settings/basic_llt.yaml b/test/settings/basic_llt.yaml new file mode 100644 index 00000000..78b79edd --- /dev/null +++ b/test/settings/basic_llt.yaml @@ -0,0 +1,9 @@ +solver_settings: + aerodynamic_model_type: LLT + density: 1.225 + type_initial_gamma_distribution: UNIFORM + +condition: + alpha: 5.0 + beta: 0.0 + wind_speed: 20.0 diff --git a/test/settings/basic_vsm.yaml b/test/settings/basic_vsm.yaml new file mode 100644 index 00000000..63dee5dc --- /dev/null +++ b/test/settings/basic_vsm.yaml @@ -0,0 +1,9 @@ +solver_settings: + aerodynamic_model_type: VSM + density: 1.225 + type_initial_gamma_distribution: UNIFORM + +condition: + alpha: 10.0 + beta: 5.0 + wind_speed: 15.0 diff --git a/test/test_settings.jl b/test/settings/test_settings.jl similarity index 82% rename from test/test_settings.jl rename to test/settings/test_settings.jl index c6e75231..4e67ce8f 100644 --- a/test/test_settings.jl +++ b/test/settings/test_settings.jl @@ -8,9 +8,9 @@ using Test @testset "Test settings.jl" begin # Change to project root directory for the test - project_root = dirname(@__DIR__) + project_root = dirname(dirname(@__DIR__)) cd(project_root) do - vss = vs("ram_air_kite/vsm_settings_dual.yaml") + vss = VSMSettings("data/ram_air_kite/vsm_settings_dual.yaml") @test vss isa VSMSettings @test vss.solver_settings isa SolverSettings @test vss.wings isa Vector{WingSettings} diff --git a/test/solver/solver_settings.yaml b/test/solver/solver_settings.yaml new file mode 100644 index 00000000..689f915a --- /dev/null +++ b/test/solver/solver_settings.yaml @@ -0,0 +1,18 @@ +wings: + - name: "solver_test_wing" + geometry_file: "test/solver/solver_test_wing.yaml" + n_panels: 4 + n_groups: 2 + spanwise_panel_distribution: COSINE + spanwise_direction: [0.0, 1.0, 0.0] + remove_nan: true + +solver_settings: + aerodynamic_model_type: VSM + density: 1.225 + type_initial_gamma_distribution: UNIFORM + +condition: + alpha: 5.0 + beta: 0.0 + wind_speed: 10.0 diff --git a/test/solver/solver_test_polar.csv b/test/solver/solver_test_polar.csv new file mode 100644 index 00000000..7e043d9c --- /dev/null +++ b/test/solver/solver_test_polar.csv @@ -0,0 +1,4 @@ +alpha,cl,cd,cm +-10.0,0.1,0.02,-0.01 +0.0,1.0,0.01,0.0 +10.0,1.8,0.025,0.01 diff --git a/test/solver/solver_test_wing.yaml b/test/solver/solver_test_wing.yaml new file mode 100644 index 00000000..fb2d9328 --- /dev/null +++ b/test/solver/solver_test_wing.yaml @@ -0,0 +1,12 @@ +wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] + +wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "solver_test_polar.csv"}] diff --git a/test/solver/test_solver.jl b/test/solver/test_solver.jl new file mode 100644 index 00000000..fecbe852 --- /dev/null +++ b/test/solver/test_solver.jl @@ -0,0 +1,34 @@ +using VortexStepMethod +using LinearAlgebra +using Test + +include("../test_data_utils.jl") + +@testset "Solver Constructor Tests" begin + @testset "Solver Constructor with VSMSettings" begin + # Use module-specific test data files + settings_file = create_temp_wing_settings("solver", "solver_test_wing.yaml"; alpha=5.0, beta=0.0, wind_speed=10.0) + + try + # Test Solver constructor with VSMSettings + settings = VSMSettings(settings_file) + wing = Wing(settings) + body_aero = BodyAerodynamics([wing]) + solver = Solver(body_aero, settings) + + # Verify solver properties match settings + @test solver.aerodynamic_model_type == VSM + @test solver.density == 1.225 + + # Test that the solver can solve + va = [10.0, 0.0, 0.0] + set_va!(body_aero, va) + sol = solve!(solver, body_aero) + @test sol isa VSMSolution + + finally + # Cleanup + rm(settings_file; force=true) + end + end +end diff --git a/test/test_data_utils.jl b/test/test_data_utils.jl new file mode 100644 index 00000000..2b6a4abb --- /dev/null +++ b/test/test_data_utils.jl @@ -0,0 +1,134 @@ +# Test data utilities for managing shared test configurations +# Organized by source module being tested + +using YAML +using Random: randstring + +""" + test_data_path(module_name, relative_path...) + +Get the absolute path to test data files relative to the test/module_name directory. + +# Arguments +- `module_name`: Name of the source module being tested (e.g., "yaml_geometry", "body_aerodynamics", "solver") +- `relative_path...`: Path components relative to the module directory + +# Examples +```julia +wing_file = test_data_path("yaml_geometry", "wings", "simple_wing.yaml") +polar_file = test_data_path("yaml_geometry", "polars", "standard_airfoil.csv") +body_aero_wing = test_data_path("body_aerodynamics", "wings", "test_wing.yaml") +``` +""" +test_data_path(module_name, relative_path...) = joinpath(@__DIR__, module_name, relative_path...) + +""" + create_temp_wing_settings(module_name, wing_file; kwargs...) + +Create a temporary VSMSettings file that references the given wing geometry file. +Useful for tests that need to modify settings while using standard wing geometries. + +# Arguments +- `module_name`: Name of the source module being tested +- `wing_file`: Wing geometry file name (relative to test/data/module_name/wings/) +- `kwargs...`: Additional settings to override defaults + +# Returns +- Path to temporary settings file (caller should clean up) + +# Example +```julia +settings_file = create_temp_wing_settings("body_aerodynamics", "test_wing.yaml"; alpha=15.0, wind_speed=25.0) +# Use settings_file... +rm(settings_file) +``` +""" +function create_temp_wing_settings(module_name, wing_file; + name="test_wing", + n_panels=4, + n_groups=2, + spanwise_panel_distribution="COSINE", + spanwise_direction=[0.0, 1.0, 0.0], + remove_nan=true, + aerodynamic_model_type="VSM", + density=1.225, + type_initial_gamma_distribution="ZEROS", + alpha=10.0, + beta=5.0, + wind_speed=15.0) + + # Use wing_file path directly if it's already an absolute path, otherwise construct it + wing_file_path = if isabspath(wing_file) + wing_file + else + test_data_path(module_name, wing_file) + end + + settings_content = """ +wings: + - name: "$name" + geometry_file: "$wing_file_path" + n_panels: $n_panels + n_groups: $n_groups + spanwise_panel_distribution: $spanwise_panel_distribution + spanwise_direction: $spanwise_direction + remove_nan: $remove_nan + +solver_settings: + aerodynamic_model_type: $aerodynamic_model_type + density: $density + type_initial_gamma_distribution: $type_initial_gamma_distribution + +condition: + alpha: $alpha + beta: $beta + wind_speed: $wind_speed +""" + + temp_file = joinpath(tempdir(), "temp_wing_settings_$(randstring(8)).yaml") + write(temp_file, settings_content) + return temp_file +end + +""" + get_standard_wing_file(module_name) + +Get the path to the standard simple wing file for a given module. + +# Example +```julia +wing_file = get_standard_wing_file("body_aerodynamics") # Returns path to test_wing.yaml +``` +""" +function get_standard_wing_file(module_name) + if module_name == "yaml_geometry" + return test_data_path("yaml_geometry", "wings", "simple_wing.yaml") + elseif module_name == "body_aerodynamics" + return test_data_path("body_aerodynamics", "wings", "test_wing.yaml") + elseif module_name == "solver" + return test_data_path("solver", "wings", "solver_test_wing.yaml") + else + error("Unknown module: $module_name") + end +end + +""" + get_complete_settings_file(module_name) + +Get the path to a complete settings file for a given module. + +# Example +```julia +settings_file = get_complete_settings_file("body_aerodynamics") +``` +""" +function get_complete_settings_file(module_name) + if module_name == "body_aerodynamics" + return test_data_path("body_aerodynamics", "complete_settings.yaml") + elseif module_name == "solver" + return test_data_path("solver", "solver_settings.yaml") + else + # Fall back to creating a temporary file + return create_temp_wing_settings(module_name, basename(get_standard_wing_file(module_name))) + end +end diff --git a/test/wake/test_wake.jl b/test/wake/test_wake.jl new file mode 100644 index 00000000..e69de29b diff --git a/test/test_wing_geometry.jl b/test/wing_geometry/test_wing_geometry.jl similarity index 100% rename from test/test_wing_geometry.jl rename to test/wing_geometry/test_wing_geometry.jl diff --git a/test/yaml_geometry/alternate_airfoil.csv b/test/yaml_geometry/alternate_airfoil.csv new file mode 100644 index 00000000..84b09166 --- /dev/null +++ b/test/yaml_geometry/alternate_airfoil.csv @@ -0,0 +1,7 @@ +alpha,cl,cd,cm +-10.0,0.15,0.025,-0.015 +-5.0,0.55,0.018,-0.008 +0.0,1.1,0.012,0.001 +5.0,1.6,0.018,0.008 +10.0,1.9,0.03,0.012 +15.0,1.7,0.055,0.018 diff --git a/test/yaml_geometry/complex_wing.yaml b/test/yaml_geometry/complex_wing.yaml new file mode 100644 index 00000000..d93dfc04 --- /dev/null +++ b/test/yaml_geometry/complex_wing.yaml @@ -0,0 +1,18 @@ +wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 5.0, 0.0, 2.0, 5.0, 0.5] + - [2, 0.2, 3.0, 0.2, 1.8, 3.0, 0.3] + - [2, 0.4, 1.0, 0.4, 1.6, 1.0, 0.1] + - [1, 0.5, 0.0, 0.5, 1.5, 0.0, 0.0] + - [2, 0.4, -1.0, 0.4, 1.6, -1.0, 0.1] + - [2, 0.2, -3.0, 0.2, 1.8, -3.0, 0.3] + - [1, 0.0, -5.0, 0.0, 2.0, -5.0, 0.5] + +wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "../standard_airfoil.csv"}] + - [2, polars, {csv_file_path: "../alternate_airfoil.csv"}] diff --git a/test/yaml_geometry/simple_wing.yaml b/test/yaml_geometry/simple_wing.yaml new file mode 100644 index 00000000..563d1425 --- /dev/null +++ b/test/yaml_geometry/simple_wing.yaml @@ -0,0 +1,12 @@ +wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] + +wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "../standard_airfoil.csv"}] diff --git a/test/yaml_geometry/standard_airfoil.csv b/test/yaml_geometry/standard_airfoil.csv new file mode 100644 index 00000000..b675b096 --- /dev/null +++ b/test/yaml_geometry/standard_airfoil.csv @@ -0,0 +1,7 @@ +alpha,cl,cd,cm +-10.0,0.1,0.02,-0.01 +-5.0,0.5,0.015,-0.005 +0.0,1.0,0.01,0.0 +5.0,1.5,0.015,0.005 +10.0,1.8,0.025,0.01 +15.0,1.6,0.05,0.015 diff --git a/test/test_yaml_geometry.jl b/test/yaml_geometry/test_yaml_geometry.jl similarity index 57% rename from test/test_yaml_geometry.jl rename to test/yaml_geometry/test_yaml_geometry.jl index f9a49406..7b838284 100644 --- a/test/test_yaml_geometry.jl +++ b/test/yaml_geometry/test_yaml_geometry.jl @@ -1,9 +1,11 @@ using VortexStepMethod -using VortexStepMethod: load_polar_data, YamlWing +using VortexStepMethod: load_polar_data using LinearAlgebra using Test using YAML +include("../test_data_utils.jl") + @testset "YAML Geometry Tests" begin # Setup temporary files for testing test_csv_path = joinpath(tempdir(), "test_polar.csv") @@ -22,12 +24,12 @@ using YAML @testset "Valid CSV File" begin # Create a valid CSV file with polar data csv_content = """alpha,cl,cd,cm --10.0,0.1,0.02,-0.01 --5.0,0.5,0.015,-0.005 -0.0,1.0,0.01,0.0 -5.0,1.5,0.015,0.005 -10.0,1.8,0.025,0.01 -15.0,1.6,0.05,0.015""" + -10.0,0.1,0.02,-0.01 + -5.0,0.5,0.015,-0.005 + 0.0,1.0,0.01,0.0 + 5.0,1.5,0.015,0.005 + 10.0,1.8,0.025,0.01 + 15.0,1.6,0.05,0.015""" write(test_csv_path, csv_content) aero_data, aero_model = load_polar_data(test_csv_path) @@ -49,9 +51,9 @@ using YAML @testset "Different Column Order" begin # Test with different column ordering csv_content = """cm,alpha,cd,cl --0.01,-10.0,0.02,0.1 --0.005,-5.0,0.015,0.5 -0.0,0.0,0.01,1.0""" + -0.01,-10.0,0.02,0.1 + -0.005,-5.0,0.015,0.5 + 0.0,0.0,0.01,1.0""" write(test_csv_path, csv_content) aero_data, aero_model = load_polar_data(test_csv_path) @@ -66,8 +68,8 @@ using YAML @testset "Case Insensitive Headers" begin # Test with mixed case headers csv_content = """ALPHA,CL,CD,CM -0.0,1.0,0.01,0.0 -5.0,1.5,0.015,0.005""" + 0.0,1.0,0.01,0.0 + 5.0,1.5,0.015,0.005""" write(test_csv_path, csv_content) aero_data, aero_model = load_polar_data(test_csv_path) @@ -94,8 +96,8 @@ using YAML @testset "Invalid CSV Format" begin # Missing required columns csv_content = """alpha,cl -0.0,1.0 -5.0,1.5""" + 0.0,1.0 + 5.0,1.5""" write(test_csv_path, csv_content) aero_data, aero_model = load_polar_data(test_csv_path) @@ -116,8 +118,8 @@ using YAML @testset "Malformed Data" begin # Invalid numeric data csv_content = """alpha,cl,cd,cm -invalid,1.0,0.01,0.0 -5.0,1.5,0.015,0.005""" + invalid,1.0,0.01,0.0 + 5.0,1.5,0.015,0.005""" write(test_csv_path, csv_content) aero_data, aero_model = load_polar_data(test_csv_path) @@ -127,7 +129,7 @@ invalid,1.0,0.01,0.0 end end - @testset "YamlWing Constructor Tests" begin + @testset "Wing Constructor Tests" begin # Create polar data directory and files mkpath(test_polar_dir) @@ -135,40 +137,44 @@ invalid,1.0,0.01,0.0 polar1_path = joinpath(test_polar_dir, "1.csv") polar2_path = joinpath(test_polar_dir, "2.csv") - polar1_content = """alpha,cl,cd,cm --10.0,0.1,0.02,-0.01 -0.0,1.0,0.01,0.0 -10.0,1.8,0.025,0.01""" - - polar2_content = """alpha,cl,cd,cm --10.0,0.15,0.025,-0.015 -0.0,1.1,0.012,0.001 -10.0,1.9,0.03,0.012""" + polar1_content = """ + alpha,cl,cd,cm + -10.0,0.1,0.02,-0.01 + 0.0,1.0,0.01,0.0 + 10.0,1.8,0.025,0.01 + """ + polar2_content = """ + alpha,cl,cd,cm + -10.0,0.15,0.025,-0.015 + 0.0,1.1,0.012,0.001 + 10.0,1.9,0.03,0.012 + """ + write(polar1_path, polar1_content) write(polar2_path, polar2_content) @testset "Valid YAML Wing Construction" begin # Create a valid YAML wing configuration yaml_content = """ -wing_sections: - headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] - data: - - [1, 0.0, 4.08, 8.05, 2.0, 4.08, 8.05] - - [2, 0.0, -4.08, 8.05, 2.0, -4.08, 8.05] - - [1, 0.0, 0.0, 4.9, 2.0, 0.0, 4.9] + wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 4.08, 8.05, 2.0, 4.08, 8.05] + - [2, 0.0, -4.08, 8.05, 2.0, -4.08, 8.05] + - [1, 0.0, 0.0, 4.9, 2.0, 0.0, 4.9] -wing_airfoils: - alpha_range: [-10, 10, 1] - reynolds: 1000000 - headers: [airfoil_id, type, info_dict] - data: - - [1, polars, {csv_file_path: "polars/1.csv"}] - - [2, polars, {csv_file_path: "polars/2.csv"}] -""" + wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "polars/1.csv"}] + - [2, polars, {csv_file_path: "polars/2.csv"}] + """ write(test_yaml_path, yaml_content) - wing = YamlWing(test_yaml_path; n_panels=4, n_groups=2) + wing = Wing(test_yaml_path; n_panels=4, n_groups=2) @test wing isa Wing @test wing.n_panels == 4 @@ -177,13 +183,15 @@ wing_airfoils: @test wing.spanwise_direction ≈ [0.0, 1.0, 0.0] @test length(wing.sections) == 3 - # Test section coordinates + # Test section coordinates (sections are sorted by spanwise position) + # Original order: [1, 0.0, 4.08, 8.05], [2, 0.0, -4.08, 8.05], [1, 0.0, 0.0, 4.9] + # Sorted by y-coordinate: y=4.08, y=0.0, y=-4.08 @test wing.sections[1].LE_point ≈ [0.0, 4.08, 8.05] @test wing.sections[1].TE_point ≈ [2.0, 4.08, 8.05] - @test wing.sections[2].LE_point ≈ [0.0, -4.08, 8.05] - @test wing.sections[2].TE_point ≈ [2.0, -4.08, 8.05] - @test wing.sections[3].LE_point ≈ [0.0, 0.0, 4.9] - @test wing.sections[3].TE_point ≈ [2.0, 0.0, 4.9] + @test wing.sections[2].LE_point ≈ [0.0, 0.0, 4.9] + @test wing.sections[2].TE_point ≈ [2.0, 0.0, 4.9] + @test wing.sections[3].LE_point ≈ [0.0, -4.08, 8.05] + @test wing.sections[3].TE_point ≈ [2.0, -4.08, 8.05] # Test that sections have polar data @test wing.sections[1].aero_model == POLAR_VECTORS @@ -198,23 +206,23 @@ wing_airfoils: @testset "Wing Constructor Parameters" begin yaml_content = """ -wing_sections: - headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] - data: - - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] - - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] + wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] -wing_airfoils: - alpha_range: [-10, 10, 1] - reynolds: 1000000 - headers: [airfoil_id, type, info_dict] - data: - - [1, polars, {csv_file_path: "polars/1.csv"}] -""" + wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "polars/1.csv"}] + """ write(test_yaml_path, yaml_content) # Test custom parameters - wing = YamlWing( + wing = Wing( test_yaml_path; n_panels=8, n_groups=4, @@ -235,6 +243,7 @@ wing_sections: headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] data: - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] wing_airfoils: alpha_range: [-10, 10, 1] @@ -245,7 +254,7 @@ wing_airfoils: """ write(test_yaml_path, yaml_content) - wing = YamlWing(test_yaml_path; n_panels=2) + wing = Wing(test_yaml_path; n_panels=2) # Should fall back to INVISCID model @test wing.sections[1].aero_model == INVISCID @@ -259,6 +268,7 @@ wing_sections: headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] data: - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] wing_airfoils: alpha_range: [-10, 10, 1] @@ -269,7 +279,7 @@ wing_airfoils: """ write(test_yaml_path, yaml_content) - wing = YamlWing(test_yaml_path; n_panels=2) + wing = Wing(test_yaml_path; n_panels=2) # Should fall back to INVISCID model @test wing.sections[1].aero_model == INVISCID @@ -281,6 +291,7 @@ wing_sections: headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] data: - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] wing_airfoils: alpha_range: [-10, 10, 1] @@ -292,10 +303,10 @@ wing_airfoils: write(test_yaml_path, yaml_content) # Test invalid n_panels/n_groups combination - @test_throws ArgumentError YamlWing(test_yaml_path; n_panels=5, n_groups=2) + @test_throws ArgumentError Wing(test_yaml_path; n_panels=5, n_groups=2) # Test invalid spanwise direction - @test_throws ArgumentError YamlWing(test_yaml_path; spanwise_direction=[1.0, 0.0, 0.0]) + @test_throws ArgumentError Wing(test_yaml_path; spanwise_direction=[1.0, 0.0, 0.0]) end @testset "Relative Path Resolution" begin @@ -312,25 +323,28 @@ wing_airfoils: # Create YAML in subdirectory with relative path subdir_yaml_path = joinpath(subdir, "wing.yaml") yaml_content = """ -wing_sections: - headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] - data: - - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] -wing_airfoils: - alpha_range: [-10, 10, 1] - reynolds: 1000000 - headers: [airfoil_id, type, info_dict] - data: - - [1, polars, {csv_file_path: "polars/airfoil.csv"}] -""" + wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "polars/airfoil.csv"}] + """ write(subdir_yaml_path, yaml_content) - wing = YamlWing(subdir_yaml_path; n_panels=2) + wing = Wing(subdir_yaml_path; n_panels=2) # Should successfully load polar data with relative path @test wing.sections[1].aero_model == POLAR_VECTORS @test wing.sections[1].aero_data isa Tuple + @test wing.sections[2].aero_model == POLAR_VECTORS + @test wing.sections[2].aero_data isa Tuple # Cleanup rm(subdir; recursive=true) @@ -339,28 +353,28 @@ wing_airfoils: @testset "Complex Wing Geometry" begin # Test with more complex wing geometry yaml_content = """ -wing_sections: - headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] - data: - - [1, 0.0, 5.0, 0.0, 2.0, 5.0, 0.5] - - [2, 0.2, 3.0, 0.2, 1.8, 3.0, 0.3] - - [2, 0.4, 1.0, 0.4, 1.6, 1.0, 0.1] - - [1, 0.5, 0.0, 0.5, 1.5, 0.0, 0.0] - - [2, 0.4, -1.0, 0.4, 1.6, -1.0, 0.1] - - [2, 0.2, -3.0, 0.2, 1.8, -3.0, 0.3] - - [1, 0.0, -5.0, 0.0, 2.0, -5.0, 0.5] + wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 5.0, 0.0, 2.0, 5.0, 0.5] + - [2, 0.2, 3.0, 0.2, 1.8, 3.0, 0.3] + - [2, 0.4, 1.0, 0.4, 1.6, 1.0, 0.1] + - [1, 0.5, 0.0, 0.5, 1.5, 0.0, 0.0] + - [2, 0.4, -1.0, 0.4, 1.6, -1.0, 0.1] + - [2, 0.2, -3.0, 0.2, 1.8, -3.0, 0.3] + - [1, 0.0, -5.0, 0.0, 2.0, -5.0, 0.5] -wing_airfoils: - alpha_range: [-10, 10, 1] - reynolds: 1000000 - headers: [airfoil_id, type, info_dict] - data: - - [1, polars, {csv_file_path: "polars/1.csv"}] - - [2, polars, {csv_file_path: "polars/2.csv"}] -""" + wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "polars/1.csv"}] + - [2, polars, {csv_file_path: "polars/2.csv"}] + """ write(test_yaml_path, yaml_content) - wing = YamlWing(test_yaml_path; n_panels=12, n_groups=3) + wing = Wing(test_yaml_path; n_panels=12, n_groups=3) @test wing.n_panels == 12 @test wing.n_groups == 3 @@ -375,6 +389,80 @@ wing_airfoils: @test wing.sections[4].LE_point[2] == 0.0 # Middle section at y=0 @test wing.sections[7].LE_point[2] == -5.0 # Last section at y=-5 end + + @testset "VSMSettings Constructor" begin + # Test Wing constructor that takes VSMSettings + yaml_content = """ + wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] + + wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "polars/1.csv"}] + """ + write(test_yaml_path, yaml_content) + + # Create VSMSettings with wing configuration + settings = VSMSettings() + settings.wings = [WingSettings( + geometry_file=test_yaml_path, + n_panels=6, + n_groups=3, + spanwise_panel_distribution=COSINE + )] + + # Test Wing constructor with VSMSettings + wing = Wing(settings) + + @test wing isa Wing + @test wing.n_panels == 6 + @test wing.n_groups == 3 + @test wing.spanwise_distribution == COSINE + @test length(wing.sections) == 2 + @test wing.sections[1].aero_model == POLAR_VECTORS + @test wing.sections[2].aero_model == POLAR_VECTORS + end + + @testset "Shared Test Data Usage" begin + # Demonstrate using module-specific test data files + simple_wing_file = test_data_path("yaml_geometry", "wings", "simple_wing.yaml") + @test isfile(simple_wing_file) + + # Test basic Wing construction with shared data + wing = Wing(simple_wing_file; n_panels=4, n_groups=2) + @test wing isa Wing + @test wing.n_panels == 4 + @test wing.n_groups == 2 + @test length(wing.sections) == 2 + + # Test complex wing construction + complex_wing_file = test_data_path("yaml_geometry", "wings", "complex_wing.yaml") + @test isfile(complex_wing_file) + + complex_wing = Wing(complex_wing_file; n_panels=12, n_groups=3) + @test complex_wing isa Wing + @test complex_wing.n_panels == 12 + @test complex_wing.n_groups == 3 + @test length(complex_wing.sections) == 7 + + # Verify polar data is loaded from shared files + @test complex_wing.sections[1].aero_model == POLAR_VECTORS + @test complex_wing.sections[1].aero_data isa Tuple + + # Test with module-specific convenience function + standard_wing_file = get_standard_wing_file("yaml_geometry") + @test isfile(standard_wing_file) + + standard_wing = Wing(standard_wing_file; n_panels=2, n_groups=1) + @test standard_wing isa Wing + @test length(standard_wing.sections) == 2 + end end # Cleanup after all tests From a26ec1e5c4c83e48701d3e4cb4e839e77422bd43 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Thu, 7 Aug 2025 12:00:30 +0200 Subject: [PATCH 18/26] #186 passing all tests now! --- test/Aqua.jl | 8 + test/README.md | 144 +++++-------- .../VortexStepMethod/test_VortexStepMethod.jl | 1 + test/filament/test_semi_infinite_filament.jl | 20 -- test/panel/test_panel.jl | 3 +- test/plotting/test_plotting.jl | 6 +- test/polars/test_polars.jl | 9 +- test/runtests.jl | 6 +- test/settings/test_settings.jl | 21 +- test/wake/test_wake.jl | 49 +++++ test/yaml_geometry/complex_wing.yaml | 4 +- test/yaml_geometry/simple_wing.yaml | 2 +- test/yaml_geometry/test_yaml_geometry.jl | 196 ++++++------------ 13 files changed, 196 insertions(+), 273 deletions(-) create mode 100644 test/Aqua.jl diff --git a/test/Aqua.jl b/test/Aqua.jl new file mode 100644 index 00000000..34474582 --- /dev/null +++ b/test/Aqua.jl @@ -0,0 +1,8 @@ +using Aqua +@testset "Aqua.jl" begin + Aqua.test_all( + VortexStepMethod; + stale_deps=(ignore=[:Xfoil, :Timers, :PyCall],), + deps_compat=(ignore=[:PyCall],) + ) +end diff --git a/test/README.md b/test/README.md index 2c7c7cba..188c01a5 100644 --- a/test/README.md +++ b/test/README.md @@ -2,103 +2,71 @@ This directory contains organized test data for the VortexStepMethod.jl test suite. -## Structure - -The test data is organized by source module being tested, following the structure of the `src/` directory: +## Running Tests +You can run tests in different ways: +```bash +# Run all tests +julia --project=. test/runtests.jl ``` -test/data/ -├── body_aerodynamics/ # Tests for src/body_aerodynamics.jl -│ ├── wings/ -│ │ └── test_wing.yaml -│ ├── polars/ -│ │ └── simple_polar.csv -│ └── complete_settings.yaml -├── yaml_geometry/ # Tests for src/yaml_geometry.jl -│ ├── wings/ -│ │ ├── simple_wing.yaml -│ │ └── complex_wing.yaml -│ └── polars/ -│ ├── standard_airfoil.csv -│ └── alternate_airfoil.csv -├── solver/ # Tests for src/solver.jl -│ ├── wings/ -│ │ └── solver_test_wing.yaml -│ ├── polars/ -│ │ └── solver_test_polar.csv -│ └── solver_settings.yaml -├── settings/ # Common settings files -│ ├── basic_vsm.yaml -│ └── basic_llt.yaml -└── wing_geometry/ # Tests for src/wing_geometry.jl (future) -``` - -## Usage - -Use the helper functions in `test_data_utils.jl` to access test data: - -### Basic Path Access -```julia -include("test_data_utils.jl") - -# Get paths to test data files -wing_file = test_data_path("yaml_geometry", "wings", "simple_wing.yaml") -polar_file = test_data_path("yaml_geometry", "polars", "standard_airfoil.csv") -settings_file = test_data_path("settings", "basic_vsm.yaml") -``` - -### Module-Specific Convenience Functions -```julia -# Get standard wing file for a module -wing_file = get_standard_wing_file("body_aerodynamics") - -# Get complete settings file for a module -settings_file = get_complete_settings_file("solver") - -# Create temporary settings with custom parameters -temp_settings = create_temp_wing_settings("yaml_geometry", "simple_wing.yaml"; - alpha=15.0, wind_speed=25.0) +```bash +# Run specific test files +julia --project=. test/yaml_geometry/test_yaml_geometry.jl +julia --project=. test/body_aerodynamics/test_body_aerodynamics.jl +julia --project=. test/solver/test_solver.jl +# etc. ``` - -## Design Principles - -1. **Module Isolation**: Each source module has its own test data directory -2. **Consistent Structure**: All modules follow the same subdirectory pattern (wings/, polars/, etc.) -3. **Reusable Components**: Common files (like basic settings) are shared in the `settings/` directory -4. **Clear Naming**: File names clearly indicate their purpose and content -5. **Self-Contained**: Each module's data is independent and can be used in isolation - ## Adding New Test Data When adding test data for a new source module: -1. Create a new directory under `test/data/` matching the source file name -2. Add subdirectories as needed (`wings/`, `polars/`, etc.) -3. Update `test_data_utils.jl` to include helper functions for the new module +1. Create test files in the appropriate module directory under `test/` +2. Add any required data files (YAML, CSV) in the same directory +3. Use `test_data_path()` helper function to access files with proper paths 4. Follow the existing naming conventions -## File Descriptions - -### Wing Geometry Files (.yaml) -- `simple_wing.yaml`: Basic 2-section wing for common tests -- `complex_wing.yaml`: Multi-section wing with multiple airfoil types -- `test_wing.yaml`: Simple wing for body aerodynamics tests -- `solver_test_wing.yaml`: Wing optimized for solver testing -### Polar Data Files (.csv) -- `standard_airfoil.csv`: Standard 6-point polar data -- `alternate_airfoil.csv`: Alternative airfoil with different coefficients -- `simple_polar.csv`: Minimal 3-point polar for basic tests -- `solver_test_polar.csv`: Polar data for solver tests +## Structure -### Settings Files (.yaml) -- `basic_vsm.yaml`: Basic VSM solver settings -- `basic_llt.yaml`: Basic LLT solver settings -- `complete_settings.yaml`: Full wing + solver configuration -- `solver_settings.yaml`: Solver-specific configuration +The test data is organized by source module being tested, following the structure of the `src/` directory: -This organization makes it easy to: -- Find test data relevant to specific source modules -- Avoid conflicts between different test requirements -- Maintain and update test data independently -- Add new test cases without affecting existing ones +``` +test/ +├── body_aerodynamics/ # Tests for src/body_aerodynamics.jl +│ ├── test_body_aerodynamics.jl +│ ├── test_results.jl +│ └── test_wing.yaml # Wing geometry for body aero tests +├── yaml_geometry/ # Tests for src/yaml_geometry.jl +│ ├── test_yaml_geometry.jl +│ ├── simple_wing.yaml # Basic 2-section wing +│ ├── complex_wing.yaml # Multi-section wing +│ ├── standard_airfoil.csv # Standard polar data +│ └── alternate_airfoil.csv # Alternative airfoil data +├── solver/ # Tests for src/solver.jl +│ ├── test_solver.jl +│ ├── solver_settings.yaml # Settings for solver tests +│ ├── solver_test_polar.csv # Polar data for solver tests +│ └── solver_test_wing.yaml # Wing for solver tests +├── settings/ # Tests for src/settings.jl +│ └── test_settings.jl +├── filament/ # Tests for src/filament.jl +│ ├── test_bound_filament.jl +│ └── test_semi_infinite_filament.jl +├── panel/ # Tests for src/panel.jl +│ └── test_panel.jl +├── plotting/ # Tests for src/plotting.jl +│ └── test_plotting.jl +├── polars/ # Tests for src/polars.jl +│ └── test_polars.jl +├── ram_geometry/ # Tests for src/ram_geometry.jl +│ └── test_kite_geometry.jl +├── wake/ # Tests for src/wake.jl +│ └── test_wake.jl +├── wing_geometry/ # Tests for src/wing_geometry.jl +│ └── test_wing_geometry.jl +├── VortexStepMethod/ # Tests for main module +│ └── test_VortexStepMethod.jl +├── test_data_utils.jl # Shared utilities for test data access +├── runtests.jl # Main test runner +└── README.md # This file +``` diff --git a/test/VortexStepMethod/test_VortexStepMethod.jl b/test/VortexStepMethod/test_VortexStepMethod.jl index e69de29b..85175440 100644 --- a/test/VortexStepMethod/test_VortexStepMethod.jl +++ b/test/VortexStepMethod/test_VortexStepMethod.jl @@ -0,0 +1 @@ +##TODO: populate \ No newline at end of file diff --git a/test/filament/test_semi_infinite_filament.jl b/test/filament/test_semi_infinite_filament.jl index 76e324cb..3355a7c2 100644 --- a/test/filament/test_semi_infinite_filament.jl +++ b/test/filament/test_semi_infinite_filament.jl @@ -41,26 +41,6 @@ end gamma = 1.0 core_radius_fraction = 0.01 work_vectors = ntuple(_ -> Vector{Float64}(undef, 3), 10) - - # @testset "Allocation Tests" begin - # filament = create_test_filament2() - # control_point = [0.5, 0.5, 2.0] - # induced_velocity = zeros(3) - # - # b = @benchmarkable velocity_3D_trailing_vortex_semiinfinite!( - # $induced_velocity, - # $filament, - # $filament.direction, - # $control_point, - # $gamma, - # $filament.vel_mag, - # $work_vectors - # ) - # result = run(b) - # @test result.allocs == 0 - # @test result.memory == 0 - # end - @testset "Calculate Induced Velocity" begin filament = create_test_filament2() control_point = [0.5, 0.5, 2.0] diff --git a/test/panel/test_panel.jl b/test/panel/test_panel.jl index 8048c548..92ec27e4 100644 --- a/test/panel/test_panel.jl +++ b/test/panel/test_panel.jl @@ -1,8 +1,7 @@ -using VortexStepMethod: Panel, Section, calculate_relative_alpha_and_relative_velocity, calculate_cl, calculate_cd_cm, reinit! +using VortexStepMethod: Panel, Section, calculate_relative_alpha_and_relative_velocity, calculate_cl, calculate_cd_cm, reinit!, INVISCID, POLAR_VECTORS, MVec3 using Interpolations: linear_interpolation, Line using LinearAlgebra using Test -# using BenchmarkTools function create_panel(section1::Section, section2::Section) # Calculate panel geometry diff --git a/test/plotting/test_plotting.jl b/test/plotting/test_plotting.jl index 7ae0b38b..8b9b2619 100644 --- a/test/plotting/test_plotting.jl +++ b/test/plotting/test_plotting.jl @@ -2,11 +2,13 @@ using VortexStepMethod using ControlPlots using Test +include("../test_data_utils.jl") + if !@isdefined ram_wing body_path = joinpath(tempdir(), "ram_air_kite_body.obj") foil_path = joinpath(tempdir(), "ram_air_kite_foil.dat") - cp("data/ram_air_kite/ram_air_kite_body.obj", body_path; force=true) - cp("data/ram_air_kite/ram_air_kite_foil.dat", foil_path; force=true) + cp("../data/ram_air_kite/ram_air_kite_body.obj", body_path; force=true) + cp("../data/ram_air_kite/ram_air_kite_foil.dat", foil_path; force=true) ram_wing = RamAirWing(body_path, foil_path; alpha_range=deg2rad.(-1:1), delta_range=deg2rad.(-1:1)) end diff --git a/test/polars/test_polars.jl b/test/polars/test_polars.jl index 89ce2df0..85175440 100644 --- a/test/polars/test_polars.jl +++ b/test/polars/test_polars.jl @@ -1,8 +1 @@ -using Aqua -@testset "Aqua.jl" begin - Aqua.test_all( - VortexStepMethod; - stale_deps=(ignore=[:Xfoil, :Timers, :PyCall],), - deps_compat=(ignore=[:PyCall],) - ) - end +##TODO: populate \ No newline at end of file diff --git a/test/runtests.jl b/test/runtests.jl index c1155d20..a6bf254f 100644 --- a/test/runtests.jl +++ b/test/runtests.jl @@ -33,10 +33,10 @@ println("Running tests...") include("ram_geometry/test_kite_geometry.jl") include("settings/test_settings.jl") include("solver/test_solver.jl") - include("solver/test_solver_results.jl") - include("wing_geometry/test_wing_settings.jl") - include("VortexStepMethod/test_vortex_step_method.jl") + include("VortexStepMethod/test_VortexStepMethod.jl") include("wake/test_wake.jl") include("wing_geometry/test_wing_geometry.jl") include("yaml_geometry/test_yaml_geometry.jl") + include("Aqua.jl") + end \ No newline at end of file diff --git a/test/settings/test_settings.jl b/test/settings/test_settings.jl index 4e67ce8f..0d2a3b3c 100644 --- a/test/settings/test_settings.jl +++ b/test/settings/test_settings.jl @@ -6,17 +6,18 @@ end using VortexStepMethod using Test +include("../test_data_utils.jl") + @testset "Test settings.jl" begin - # Change to project root directory for the test + # Use the absolute path to test data to avoid path concatenation issues project_root = dirname(dirname(@__DIR__)) - cd(project_root) do - vss = VSMSettings("data/ram_air_kite/vsm_settings_dual.yaml") - @test vss isa VSMSettings - @test vss.solver_settings isa SolverSettings - @test vss.wings isa Vector{WingSettings} - @test length(vss.wings) == 2 - io = IOBuffer(repr(vss)) - @test countlines(io) == 40 # Updated to match new output format - end + settings_file = joinpath(project_root, "data", "ram_air_kite", "vsm_settings_dual.yaml") + vss = VSMSettings(settings_file) + @test vss isa VSMSettings + @test vss.solver_settings isa SolverSettings + @test vss.wings isa Vector{WingSettings} + @test length(vss.wings) == 2 + io = IOBuffer(repr(vss)) + @test countlines(io) == 40 # Updated to match new output format end nothing diff --git a/test/wake/test_wake.jl b/test/wake/test_wake.jl index e69de29b..156e4ec9 100644 --- a/test/wake/test_wake.jl +++ b/test/wake/test_wake.jl @@ -0,0 +1,49 @@ +using Test +using LinearAlgebra +using VortexStepMethod + +# Test the actual frozen_wake! function using real objects +@testset "frozen_wake! Tests" begin + @testset "frozen_wake! basic functionality" begin + # Use existing test data that we know works + data_dir = joinpath(dirname(dirname(@__DIR__)), "data", "ram_air_kite") + body_path = joinpath(tempdir(), "ram_air_kite_body.obj") + foil_path = joinpath(tempdir(), "ram_air_kite_foil.dat") + + body_src = joinpath(data_dir, "ram_air_kite_body.obj") + foil_src = joinpath(data_dir, "ram_air_kite_foil.dat") + + # Check if source files exist before copying + if isfile(body_src) && isfile(foil_src) + cp(body_src, body_path; force=true) + cp(foil_src, foil_path; force=true) + + try + # Create wing and body aerodynamics with known good geometry + wing = RamAirWing(body_path, foil_path; n_panels=56) # Use default panels + body_aero = BodyAerodynamics([wing]) + + # Test that frozen_wake! doesn't throw errors + n_panels = length(body_aero.panels) + va_distribution = ones(n_panels, 3) # Create velocity distribution for all panels + va_distribution[:, 1] .= 15.0 # X velocity = 15.0 m/s + va_distribution[:, 2] .= 0.0 # Y velocity = 0.0 + va_distribution[:, 3] .= 0.0 # Z velocity = 0.0 + + # This should not throw an error + @test_nowarn VortexStepMethod.frozen_wake!(body_aero, va_distribution) + + # Test that the function accepts the right number of velocity vectors + @test size(va_distribution, 1) == length(body_aero.panels) + @test size(va_distribution, 2) == 3 # 3D velocity vectors + + finally + # Clean up + rm(body_path; force=true) + rm(foil_path; force=true) + end + else + @test_skip "Ram air kite test data files not found, skipping frozen_wake! test" + end + end +end diff --git a/test/yaml_geometry/complex_wing.yaml b/test/yaml_geometry/complex_wing.yaml index d93dfc04..ff38435d 100644 --- a/test/yaml_geometry/complex_wing.yaml +++ b/test/yaml_geometry/complex_wing.yaml @@ -14,5 +14,5 @@ wing_airfoils: reynolds: 1000000 headers: [airfoil_id, type, info_dict] data: - - [1, polars, {csv_file_path: "../standard_airfoil.csv"}] - - [2, polars, {csv_file_path: "../alternate_airfoil.csv"}] + - [1, polars, {csv_file_path: "standard_airfoil.csv"}] + - [2, polars, {csv_file_path: "alternate_airfoil.csv"}] diff --git a/test/yaml_geometry/simple_wing.yaml b/test/yaml_geometry/simple_wing.yaml index 563d1425..e6c62baa 100644 --- a/test/yaml_geometry/simple_wing.yaml +++ b/test/yaml_geometry/simple_wing.yaml @@ -9,4 +9,4 @@ wing_airfoils: reynolds: 1000000 headers: [airfoil_id, type, info_dict] data: - - [1, polars, {csv_file_path: "../standard_airfoil.csv"}] + - [1, polars, {csv_file_path: "standard_airfoil.csv"}] diff --git a/test/yaml_geometry/test_yaml_geometry.jl b/test/yaml_geometry/test_yaml_geometry.jl index 7b838284..fdc9429b 100644 --- a/test/yaml_geometry/test_yaml_geometry.jl +++ b/test/yaml_geometry/test_yaml_geometry.jl @@ -3,9 +3,21 @@ using VortexStepMethod: load_polar_data using LinearAlgebra using Test using YAML +using Logging include("../test_data_utils.jl") +# Helper function to suppress expected warnings during tests +function suppress_warnings(f) + old_logger = global_logger() + try + global_logger(NullLogger()) + return f() + finally + global_logger(old_logger) + end +end + @testset "YAML Geometry Tests" begin # Setup temporary files for testing test_csv_path = joinpath(tempdir(), "test_polar.csv") @@ -14,10 +26,13 @@ include("../test_data_utils.jl") # Clean up function function cleanup_test_files() - for file in [test_csv_path, test_yaml_path] - isfile(file) && rm(file) + test_dir = dirname(test_yaml_path) + for file in [test_csv_path, test_yaml_path, + joinpath(test_dir, "standard_airfoil.csv"), + joinpath(test_dir, "alternate_airfoil.csv")] + isfile(file) && rm(file; force=true) end - isdir(test_polar_dir) && rm(test_polar_dir; recursive=true) + isdir(test_polar_dir) && rm(test_polar_dir; recursive=true, force=true) end @testset "load_polar_data Function Tests" begin @@ -80,14 +95,14 @@ include("../test_data_utils.jl") @testset "Missing File" begin nonexistent_path = joinpath(tempdir(), "nonexistent.csv") - aero_data, aero_model = load_polar_data(nonexistent_path) + aero_data, aero_model = suppress_warnings(() -> load_polar_data(nonexistent_path)) @test aero_model == INVISCID @test aero_data === nothing end @testset "Empty File Path" begin - aero_data, aero_model = load_polar_data("") + aero_data, aero_model = suppress_warnings(() -> load_polar_data("")) @test aero_model == INVISCID @test aero_data === nothing @@ -100,7 +115,7 @@ include("../test_data_utils.jl") 5.0,1.5""" write(test_csv_path, csv_content) - aero_data, aero_model = load_polar_data(test_csv_path) + aero_data, aero_model = suppress_warnings(() -> load_polar_data(test_csv_path)) @test aero_model == INVISCID @test aero_data === nothing @@ -109,7 +124,7 @@ include("../test_data_utils.jl") @testset "Empty CSV File" begin write(test_csv_path, "") - aero_data, aero_model = load_polar_data(test_csv_path) + aero_data, aero_model = suppress_warnings(() -> load_polar_data(test_csv_path)) @test aero_model == INVISCID @test aero_data === nothing @@ -122,7 +137,7 @@ include("../test_data_utils.jl") 5.0,1.5,0.015,0.005""" write(test_csv_path, csv_content) - aero_data, aero_model = load_polar_data(test_csv_path) + aero_data, aero_model = suppress_warnings(() -> load_polar_data(test_csv_path)) @test aero_model == INVISCID @test aero_data === nothing @@ -133,46 +148,18 @@ include("../test_data_utils.jl") # Create polar data directory and files mkpath(test_polar_dir) - # Create polar files - polar1_path = joinpath(test_polar_dir, "1.csv") - polar2_path = joinpath(test_polar_dir, "2.csv") + # Copy the actual polar files to the temp directory for tests that reference them + cp(test_data_path("yaml_geometry", "standard_airfoil.csv"), joinpath(test_polar_dir, "1.csv"); force=true) + cp(test_data_path("yaml_geometry", "alternate_airfoil.csv"), joinpath(test_polar_dir, "2.csv"); force=true) - polar1_content = """ - alpha,cl,cd,cm - -10.0,0.1,0.02,-0.01 - 0.0,1.0,0.01,0.0 - 10.0,1.8,0.025,0.01 - """ - - polar2_content = """ - alpha,cl,cd,cm - -10.0,0.15,0.025,-0.015 - 0.0,1.1,0.012,0.001 - 10.0,1.9,0.03,0.012 - """ - - write(polar1_path, polar1_content) - write(polar2_path, polar2_content) + # Also copy them to the test directory itself for direct reference tests + test_dir = dirname(test_yaml_path) + cp(test_data_path("yaml_geometry", "standard_airfoil.csv"), joinpath(test_dir, "standard_airfoil.csv"); force=true) + cp(test_data_path("yaml_geometry", "alternate_airfoil.csv"), joinpath(test_dir, "alternate_airfoil.csv"); force=true) @testset "Valid YAML Wing Construction" begin - # Create a valid YAML wing configuration - yaml_content = """ - wing_sections: - headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] - data: - - [1, 0.0, 4.08, 8.05, 2.0, 4.08, 8.05] - - [2, 0.0, -4.08, 8.05, 2.0, -4.08, 8.05] - - [1, 0.0, 0.0, 4.9, 2.0, 0.0, 4.9] - - wing_airfoils: - alpha_range: [-10, 10, 1] - reynolds: 1000000 - headers: [airfoil_id, type, info_dict] - data: - - [1, polars, {csv_file_path: "polars/1.csv"}] - - [2, polars, {csv_file_path: "polars/2.csv"}] - """ - write(test_yaml_path, yaml_content) + # Use the actual YAML file from the test data + cp(test_data_path("yaml_geometry", "simple_wing.yaml"), test_yaml_path; force=true) wing = Wing(test_yaml_path; n_panels=4, n_groups=2) @@ -181,45 +168,29 @@ include("../test_data_utils.jl") @test wing.n_groups == 2 @test wing.spanwise_distribution == LINEAR @test wing.spanwise_direction ≈ [0.0, 1.0, 0.0] - @test length(wing.sections) == 3 + @test length(wing.sections) == 2 # simple_wing has 2 sections # Test section coordinates (sections are sorted by spanwise position) - # Original order: [1, 0.0, 4.08, 8.05], [2, 0.0, -4.08, 8.05], [1, 0.0, 0.0, 4.9] - # Sorted by y-coordinate: y=4.08, y=0.0, y=-4.08 - @test wing.sections[1].LE_point ≈ [0.0, 4.08, 8.05] - @test wing.sections[1].TE_point ≈ [2.0, 4.08, 8.05] - @test wing.sections[2].LE_point ≈ [0.0, 0.0, 4.9] - @test wing.sections[2].TE_point ≈ [2.0, 0.0, 4.9] - @test wing.sections[3].LE_point ≈ [0.0, -4.08, 8.05] - @test wing.sections[3].TE_point ≈ [2.0, -4.08, 8.05] + # simple_wing.yaml has: [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] and [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] + # Sorted by y-coordinate: y=1.0, y=-1.0 + @test wing.sections[1].LE_point ≈ [0.0, 1.0, 0.0] + @test wing.sections[1].TE_point ≈ [1.0, 1.0, 0.0] + @test wing.sections[2].LE_point ≈ [0.0, -1.0, 0.0] + @test wing.sections[2].TE_point ≈ [1.0, -1.0, 0.0] # Test that sections have polar data @test wing.sections[1].aero_model == POLAR_VECTORS @test wing.sections[2].aero_model == POLAR_VECTORS - @test wing.sections[3].aero_model == POLAR_VECTORS # Test polar data is loaded @test wing.sections[1].aero_data isa Tuple @test length(wing.sections[1].aero_data) == 4 - @test length(wing.sections[1].aero_data[1]) == 3 # 3 alpha points + @test length(wing.sections[1].aero_data[1]) >= 3 # at least 3 alpha points end @testset "Wing Constructor Parameters" begin - yaml_content = """ - wing_sections: - headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] - data: - - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] - - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] - - wing_airfoils: - alpha_range: [-10, 10, 1] - reynolds: 1000000 - headers: [airfoil_id, type, info_dict] - data: - - [1, polars, {csv_file_path: "polars/1.csv"}] - """ - write(test_yaml_path, yaml_content) + # Use the simple_wing.yaml and test custom parameters + cp(test_data_path("yaml_geometry", "simple_wing.yaml"), test_yaml_path; force=true) # Test custom parameters wing = Wing( @@ -254,7 +225,7 @@ wing_airfoils: """ write(test_yaml_path, yaml_content) - wing = Wing(test_yaml_path; n_panels=2) + wing = suppress_warnings(() -> Wing(test_yaml_path; n_panels=2)) # Should fall back to INVISCID model @test wing.sections[1].aero_model == INVISCID @@ -279,7 +250,7 @@ wing_airfoils: """ write(test_yaml_path, yaml_content) - wing = Wing(test_yaml_path; n_panels=2) + wing = suppress_warnings(() -> Wing(test_yaml_path; n_panels=2)) # Should fall back to INVISCID model @test wing.sections[1].aero_model == INVISCID @@ -313,30 +284,14 @@ wing_airfoils: # Test that relative paths in CSV files are resolved relative to YAML file subdir = joinpath(tempdir(), "subtest") mkpath(subdir) - subdir_polar_dir = joinpath(subdir, "polars") - mkpath(subdir_polar_dir) - - # Create polar file in subdirectory - subdir_polar_path = joinpath(subdir_polar_dir, "airfoil.csv") - write(subdir_polar_path, polar1_content) - # Create YAML in subdirectory with relative path + # Copy the simple wing file to subdirectory subdir_yaml_path = joinpath(subdir, "wing.yaml") - yaml_content = """ - wing_sections: - headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] - data: - - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] - - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] - - wing_airfoils: - alpha_range: [-10, 10, 1] - reynolds: 1000000 - headers: [airfoil_id, type, info_dict] - data: - - [1, polars, {csv_file_path: "polars/airfoil.csv"}] - """ - write(subdir_yaml_path, yaml_content) + cp(test_data_path("yaml_geometry", "simple_wing.yaml"), subdir_yaml_path; force=true) + + # Copy the polar file to subdirectory too + subdir_polar_path = joinpath(subdir, "standard_airfoil.csv") + cp(test_data_path("yaml_geometry", "standard_airfoil.csv"), subdir_polar_path; force=true) wing = Wing(subdir_yaml_path; n_panels=2) @@ -351,28 +306,8 @@ wing_airfoils: end @testset "Complex Wing Geometry" begin - # Test with more complex wing geometry - yaml_content = """ - wing_sections: - headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] - data: - - [1, 0.0, 5.0, 0.0, 2.0, 5.0, 0.5] - - [2, 0.2, 3.0, 0.2, 1.8, 3.0, 0.3] - - [2, 0.4, 1.0, 0.4, 1.6, 1.0, 0.1] - - [1, 0.5, 0.0, 0.5, 1.5, 0.0, 0.0] - - [2, 0.4, -1.0, 0.4, 1.6, -1.0, 0.1] - - [2, 0.2, -3.0, 0.2, 1.8, -3.0, 0.3] - - [1, 0.0, -5.0, 0.0, 2.0, -5.0, 0.5] - - wing_airfoils: - alpha_range: [-10, 10, 1] - reynolds: 1000000 - headers: [airfoil_id, type, info_dict] - data: - - [1, polars, {csv_file_path: "polars/1.csv"}] - - [2, polars, {csv_file_path: "polars/2.csv"}] - """ - write(test_yaml_path, yaml_content) + # Use the actual complex_wing.yaml file + cp(test_data_path("yaml_geometry", "complex_wing.yaml"), test_yaml_path; force=true) wing = Wing(test_yaml_path; n_panels=12, n_groups=3) @@ -392,26 +327,13 @@ wing_airfoils: @testset "VSMSettings Constructor" begin # Test Wing constructor that takes VSMSettings - yaml_content = """ - wing_sections: - headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] - data: - - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] - - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] - - wing_airfoils: - alpha_range: [-10, 10, 1] - reynolds: 1000000 - headers: [airfoil_id, type, info_dict] - data: - - [1, polars, {csv_file_path: "polars/1.csv"}] - """ - write(test_yaml_path, yaml_content) + # Use the actual simple_wing.yaml file + simple_wing_file = test_data_path("yaml_geometry", "simple_wing.yaml") # Create VSMSettings with wing configuration settings = VSMSettings() settings.wings = [WingSettings( - geometry_file=test_yaml_path, + geometry_file=simple_wing_file, n_panels=6, n_groups=3, spanwise_panel_distribution=COSINE @@ -431,7 +353,7 @@ wing_airfoils: @testset "Shared Test Data Usage" begin # Demonstrate using module-specific test data files - simple_wing_file = test_data_path("yaml_geometry", "wings", "simple_wing.yaml") + simple_wing_file = test_data_path("yaml_geometry", "simple_wing.yaml") @test isfile(simple_wing_file) # Test basic Wing construction with shared data @@ -442,7 +364,7 @@ wing_airfoils: @test length(wing.sections) == 2 # Test complex wing construction - complex_wing_file = test_data_path("yaml_geometry", "wings", "complex_wing.yaml") + complex_wing_file = test_data_path("yaml_geometry", "complex_wing.yaml") @test isfile(complex_wing_file) complex_wing = Wing(complex_wing_file; n_panels=12, n_groups=3) @@ -455,8 +377,8 @@ wing_airfoils: @test complex_wing.sections[1].aero_model == POLAR_VECTORS @test complex_wing.sections[1].aero_data isa Tuple - # Test with module-specific convenience function - standard_wing_file = get_standard_wing_file("yaml_geometry") + # Test with module-specific convenience function - create a standard wing for this test + standard_wing_file = simple_wing_file # Use simple_wing as our "standard" @test isfile(standard_wing_file) standard_wing = Wing(standard_wing_file; n_panels=2, n_groups=1) From 38f910599413c5fd833a5a669456c5233138f778 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Thu, 7 Aug 2025 12:25:53 +0200 Subject: [PATCH 19/26] # 186 Adding random to toml --- Project.toml | 4 +++- test/data/README.md | 0 test/data/body_aerodynamics/complete_settings.yaml | 0 test/data/body_aerodynamics/polars/simple_polar.csv | 0 test/data/body_aerodynamics/wings/test_wing.yaml | 0 test/data/settings/basic_llt.yaml | 0 test/data/settings/basic_llt_settings.yaml | 0 test/data/settings/basic_vsm.yaml | 0 test/data/settings/basic_vsm_settings.yaml | 0 test/data/settings/complete_wing_settings.yaml | 0 test/data/solver/polars/solver_test_polar.csv | 0 test/data/solver/solver_settings.yaml | 0 test/data/solver/wings/solver_test_wing.yaml | 0 test/data/wings/complex_wing.yaml | 0 test/data/wings/polars/test_polar_1.csv | 0 test/data/wings/polars/test_polar_2.csv | 0 test/data/wings/simple_wing.yaml | 0 test/data/yaml_geometry/polars/alternate_airfoil.csv | 0 test/data/yaml_geometry/polars/standard_airfoil.csv | 0 test/data/yaml_geometry/wings/complex_wing.yaml | 0 test/data/yaml_geometry/wings/simple_wing.yaml | 0 test/test_body_aerodynamics.jl | 0 test/test_solver.jl | 0 test/test_yaml_geometry.jl | 0 test/yaml_geometry/wings/complex_wing.yaml | 0 test/yaml_geometry/wings/simple_wing.yaml | 0 26 files changed, 3 insertions(+), 1 deletion(-) create mode 100644 test/data/README.md create mode 100644 test/data/body_aerodynamics/complete_settings.yaml create mode 100644 test/data/body_aerodynamics/polars/simple_polar.csv create mode 100644 test/data/body_aerodynamics/wings/test_wing.yaml create mode 100644 test/data/settings/basic_llt.yaml create mode 100644 test/data/settings/basic_llt_settings.yaml create mode 100644 test/data/settings/basic_vsm.yaml create mode 100644 test/data/settings/basic_vsm_settings.yaml create mode 100644 test/data/settings/complete_wing_settings.yaml create mode 100644 test/data/solver/polars/solver_test_polar.csv create mode 100644 test/data/solver/solver_settings.yaml create mode 100644 test/data/solver/wings/solver_test_wing.yaml create mode 100644 test/data/wings/complex_wing.yaml create mode 100644 test/data/wings/polars/test_polar_1.csv create mode 100644 test/data/wings/polars/test_polar_2.csv create mode 100644 test/data/wings/simple_wing.yaml create mode 100644 test/data/yaml_geometry/polars/alternate_airfoil.csv create mode 100644 test/data/yaml_geometry/polars/standard_airfoil.csv create mode 100644 test/data/yaml_geometry/wings/complex_wing.yaml create mode 100644 test/data/yaml_geometry/wings/simple_wing.yaml create mode 100644 test/test_body_aerodynamics.jl create mode 100644 test/test_solver.jl create mode 100644 test/test_yaml_geometry.jl create mode 100644 test/yaml_geometry/wings/complex_wing.yaml create mode 100644 test/yaml_geometry/wings/simple_wing.yaml diff --git a/Project.toml b/Project.toml index c7e7cd2e..76741e50 100644 --- a/Project.toml +++ b/Project.toml @@ -56,6 +56,7 @@ Parameters = "0.12" Pkg = "1" PreallocationTools = "0.4.25" PrecompileTools = "1.2.1" +Random = "1.11.0" SciMLBase = "2.77.0" Serialization = "1" StaticArrays = "1" @@ -74,7 +75,8 @@ CSV = "336ed68f-0bac-5ca0-87d4-7b16caf5d00b" ControlPlots = "23c2ee80-7a9e-4350-b264-8e670f12517c" DataFrames = "a93c6f00-e57d-5684-b7b6-d8193f3e46c0" Documenter = "e30172f5-a6a5-5a46-863b-614d45cd2de4" +Random = "9a3f8284-a2c9-5f02-9a11-845980a1fd5c" Test = "8dfed614-e22c-5e08-85e1-65c5234f0b40" [targets] -test = ["Test", "DataFrames", "CSV", "Documenter", "BenchmarkTools", "ControlPlots", "Aqua"] +test = ["Test", "DataFrames", "CSV", "Documenter", "BenchmarkTools", "ControlPlots", "Aqua", "Random"] diff --git a/test/data/README.md b/test/data/README.md new file mode 100644 index 00000000..e69de29b diff --git a/test/data/body_aerodynamics/complete_settings.yaml b/test/data/body_aerodynamics/complete_settings.yaml new file mode 100644 index 00000000..e69de29b diff --git a/test/data/body_aerodynamics/polars/simple_polar.csv b/test/data/body_aerodynamics/polars/simple_polar.csv new file mode 100644 index 00000000..e69de29b diff --git a/test/data/body_aerodynamics/wings/test_wing.yaml b/test/data/body_aerodynamics/wings/test_wing.yaml new file mode 100644 index 00000000..e69de29b diff --git a/test/data/settings/basic_llt.yaml b/test/data/settings/basic_llt.yaml new file mode 100644 index 00000000..e69de29b diff --git a/test/data/settings/basic_llt_settings.yaml b/test/data/settings/basic_llt_settings.yaml new file mode 100644 index 00000000..e69de29b diff --git a/test/data/settings/basic_vsm.yaml b/test/data/settings/basic_vsm.yaml new file mode 100644 index 00000000..e69de29b diff --git a/test/data/settings/basic_vsm_settings.yaml b/test/data/settings/basic_vsm_settings.yaml new file mode 100644 index 00000000..e69de29b diff --git a/test/data/settings/complete_wing_settings.yaml b/test/data/settings/complete_wing_settings.yaml new file mode 100644 index 00000000..e69de29b diff --git a/test/data/solver/polars/solver_test_polar.csv b/test/data/solver/polars/solver_test_polar.csv new file mode 100644 index 00000000..e69de29b diff --git a/test/data/solver/solver_settings.yaml b/test/data/solver/solver_settings.yaml new file mode 100644 index 00000000..e69de29b diff --git a/test/data/solver/wings/solver_test_wing.yaml b/test/data/solver/wings/solver_test_wing.yaml new file mode 100644 index 00000000..e69de29b diff --git a/test/data/wings/complex_wing.yaml b/test/data/wings/complex_wing.yaml new file mode 100644 index 00000000..e69de29b diff --git a/test/data/wings/polars/test_polar_1.csv b/test/data/wings/polars/test_polar_1.csv new file mode 100644 index 00000000..e69de29b diff --git a/test/data/wings/polars/test_polar_2.csv b/test/data/wings/polars/test_polar_2.csv new file mode 100644 index 00000000..e69de29b diff --git a/test/data/wings/simple_wing.yaml b/test/data/wings/simple_wing.yaml new file mode 100644 index 00000000..e69de29b diff --git a/test/data/yaml_geometry/polars/alternate_airfoil.csv b/test/data/yaml_geometry/polars/alternate_airfoil.csv new file mode 100644 index 00000000..e69de29b diff --git a/test/data/yaml_geometry/polars/standard_airfoil.csv b/test/data/yaml_geometry/polars/standard_airfoil.csv new file mode 100644 index 00000000..e69de29b diff --git a/test/data/yaml_geometry/wings/complex_wing.yaml b/test/data/yaml_geometry/wings/complex_wing.yaml new file mode 100644 index 00000000..e69de29b diff --git a/test/data/yaml_geometry/wings/simple_wing.yaml b/test/data/yaml_geometry/wings/simple_wing.yaml new file mode 100644 index 00000000..e69de29b diff --git a/test/test_body_aerodynamics.jl b/test/test_body_aerodynamics.jl new file mode 100644 index 00000000..e69de29b diff --git a/test/test_solver.jl b/test/test_solver.jl new file mode 100644 index 00000000..e69de29b diff --git a/test/test_yaml_geometry.jl b/test/test_yaml_geometry.jl new file mode 100644 index 00000000..e69de29b diff --git a/test/yaml_geometry/wings/complex_wing.yaml b/test/yaml_geometry/wings/complex_wing.yaml new file mode 100644 index 00000000..e69de29b diff --git a/test/yaml_geometry/wings/simple_wing.yaml b/test/yaml_geometry/wings/simple_wing.yaml new file mode 100644 index 00000000..e69de29b From c36f5e66fbdeda8c9639ad4232601bde79dde137 Mon Sep 17 00:00:00 2001 From: 1-Bart-1 Date: Thu, 7 Aug 2025 15:12:52 +0200 Subject: [PATCH 20/26] Update manifest --- Manifest-v1.11.toml.default | 311 ++++++++++++++++++++++-------------- 1 file changed, 195 insertions(+), 116 deletions(-) diff --git a/Manifest-v1.11.toml.default b/Manifest-v1.11.toml.default index 076203da..461b3127 100644 --- a/Manifest-v1.11.toml.default +++ b/Manifest-v1.11.toml.default @@ -1,13 +1,13 @@ # This file is machine-generated - editing it directly is not advised -julia_version = "1.11.4" +julia_version = "1.11.6" manifest_format = "2.0" -project_hash = "8aabd59bb81f00c0149c8b45c84ed6c3038dd1c6" +project_hash = "af9326657e0997d9341c6ceac49c14579de5e965" [[deps.ADTypes]] -git-tree-sha1 = "e2478490447631aedba0823d4d7a80b2cc8cdb32" +git-tree-sha1 = "7927b9af540ee964cc5d1b73293f1eb0b761a3a1" uuid = "47edcb42-4c32-4615-8424-f2b9edc5f35b" -version = "1.14.0" +version = "1.16.0" weakdeps = ["ChainRulesCore", "ConstructionBase", "EnzymeCore"] [deps.ADTypes.extensions] @@ -41,9 +41,9 @@ version = "0.1.42" [[deps.Adapt]] deps = ["LinearAlgebra", "Requires"] -git-tree-sha1 = "cd8b948862abee8f3d3e9b73a102a9ca924debb0" +git-tree-sha1 = "f7817e2e585aa6d924fd714df1e2a84be7896c60" uuid = "79e6a3ab-5dfb-504d-930d-738a2a938a0e" -version = "4.2.0" +version = "4.3.0" weakdeps = ["SparseArrays", "StaticArrays"] [deps.Adapt.extensions] @@ -56,9 +56,9 @@ version = "1.1.2" [[deps.ArrayInterface]] deps = ["Adapt", "LinearAlgebra"] -git-tree-sha1 = "017fcb757f8e921fb44ee063a7aafe5f89b86dd1" +git-tree-sha1 = "9606d7832795cbef89e06a550475be300364a8aa" uuid = "4fba245c-0d91-5ea0-9b3e-6abc04ee57a9" -version = "7.18.0" +version = "7.19.0" [deps.ArrayInterface.extensions] ArrayInterfaceBandedMatricesExt = "BandedMatrices" @@ -87,10 +87,10 @@ version = "7.18.0" Tracker = "9f7883ad-71c0-57eb-9f7f-b5c9e6d3789c" [[deps.ArrayLayouts]] -deps = ["FillArrays", "LinearAlgebra"] -git-tree-sha1 = "4e25216b8fea1908a0ce0f5d87368587899f75be" +deps = ["FillArrays", "LinearAlgebra", "StaticArrays"] +git-tree-sha1 = "120e392af69350960b1d3b89d41dcc1d66543858" uuid = "4c555306-a7a7-4459-81d9-ec55ddd5c99a" -version = "1.11.1" +version = "1.11.2" weakdeps = ["SparseArrays"] [deps.ArrayLayouts.extensions] @@ -118,12 +118,13 @@ version = "0.1.6" [[deps.BracketingNonlinearSolve]] deps = ["CommonSolve", "ConcreteStructs", "NonlinearSolveBase", "PrecompileTools", "Reexport", "SciMLBase"] -git-tree-sha1 = "95cb19c37ea427617e9795655667712f03058d98" +git-tree-sha1 = "a9014924595b7a2c1dd14aac516e38fa10ada656" uuid = "70df07ce-3d50-431d-a3e7-ca6ddb60ac1e" -version = "1.1.0" -weakdeps = ["ForwardDiff"] +version = "1.3.0" +weakdeps = ["ChainRulesCore", "ForwardDiff"] [deps.BracketingNonlinearSolve.extensions] + BracketingNonlinearSolveChainRulesCoreExt = ["ChainRulesCore", "ForwardDiff"] BracketingNonlinearSolveForwardDiffExt = "ForwardDiff" [[deps.CPUSummary]] @@ -134,9 +135,9 @@ version = "0.2.6" [[deps.ChainRulesCore]] deps = ["Compat", "LinearAlgebra"] -git-tree-sha1 = "1713c74e00545bfe14605d2a2be1712de8fbcb58" +git-tree-sha1 = "06ee8d1aa558d2833aa799f6f0b31b30cada405f" uuid = "d360d2e6-b24c-11e9-a2a3-2a2ae2dbcce4" -version = "1.25.1" +version = "1.25.2" weakdeps = ["SparseArrays"] [deps.ChainRulesCore.extensions] @@ -150,9 +151,9 @@ version = "0.1.13" [[deps.ColorTypes]] deps = ["FixedPointNumbers", "Random"] -git-tree-sha1 = "c7acce7a7e1078a20a285211dd73cd3941a871d6" +git-tree-sha1 = "67e11ee83a43eb71ddc950302c53bf33f0690dfe" uuid = "3da002f7-5984-5a60-b8a6-cbb66c0b333f" -version = "0.12.0" +version = "0.12.1" [deps.ColorTypes.extensions] StyledStringsExt = "StyledStrings" @@ -162,9 +163,9 @@ version = "0.12.0" [[deps.Colors]] deps = ["ColorTypes", "FixedPointNumbers", "Reexport"] -git-tree-sha1 = "64e15186f0aa277e174aa81798f7eb8598e0157e" +git-tree-sha1 = "37ea44092930b1811e666c3bc38065d7d87fcc74" uuid = "5ae59095-9a9b-59fe-a467-6f913c188581" -version = "0.13.0" +version = "0.13.1" [[deps.CommonSolve]] git-tree-sha1 = "0eee5eb66b1cf62cd6ad1b460238e60e4b09400c" @@ -184,9 +185,9 @@ version = "1.0.0" [[deps.Compat]] deps = ["TOML", "UUIDs"] -git-tree-sha1 = "8ae8d32e09f0dcf42a36b90d4e17f5dd2e4c4215" +git-tree-sha1 = "0037835448781bb46feb39866934e243886d756a" uuid = "34da2185-b29b-5c13-b0c7-acf172513d20" -version = "4.16.0" +version = "4.18.0" weakdeps = ["Dates", "LinearAlgebra"] [deps.Compat.extensions] @@ -212,9 +213,9 @@ uuid = "2569d6c7-a4a2-43d3-a901-331e8e4be471" version = "0.2.3" [[deps.ConstructionBase]] -git-tree-sha1 = "76219f1ed5771adbb096743bff43fb5fdd4c1157" +git-tree-sha1 = "b4b092499347b18a015186eae3042f72267106cb" uuid = "187b0558-2788-49d3-abe0-74a17ed4e7c9" -version = "1.5.8" +version = "1.6.0" [deps.ConstructionBase.extensions] ConstructionBaseIntervalSetsExt = "IntervalSets" @@ -232,16 +233,21 @@ git-tree-sha1 = "fcbb72b032692610bfbdb15018ac16a36cf2e406" uuid = "adafc99b-e345-5852-983c-f28acb93d879" version = "0.3.1" +[[deps.Crayons]] +git-tree-sha1 = "249fe38abf76d48563e2f4556bebd215aa317e15" +uuid = "a8cc5b0e-0ffa-5ad4-8c14-923d3ee1735f" +version = "4.1.1" + [[deps.DataAPI]] git-tree-sha1 = "abe83f3a2f1b857aac70ef8b269080af17764bbe" uuid = "9a962f9c-6df0-11e9-0e5d-c546b8b5ee8a" version = "1.16.0" [[deps.DataStructures]] -deps = ["Compat", "InteractiveUtils", "OrderedCollections"] -git-tree-sha1 = "1d0a14036acb104d9e89698bd408f63ab58cdc82" +deps = ["OrderedCollections"] +git-tree-sha1 = "76b3b7c3925d943edf158ddb7f693ba54eb297a5" uuid = "864edb3b-99cc-5e75-8d2d-829cb0a9cfe8" -version = "0.18.20" +version = "0.19.0" [[deps.DataValueInterfaces]] git-tree-sha1 = "bfc1187b79289637fa0ef6d4436ebdfe6905cbd6" @@ -266,10 +272,10 @@ uuid = "8bb1440f-4735-579b-a4ab-409b98df4dab" version = "1.9.1" [[deps.DiffEqBase]] -deps = ["ArrayInterface", "ConcreteStructs", "DataStructures", "DocStringExtensions", "EnumX", "EnzymeCore", "FastBroadcast", "FastClosures", "FastPower", "FunctionWrappers", "FunctionWrappersWrappers", "LinearAlgebra", "Logging", "Markdown", "MuladdMacro", "Parameters", "PrecompileTools", "Printf", "RecursiveArrayTools", "Reexport", "SciMLBase", "SciMLOperators", "SciMLStructures", "Setfield", "Static", "StaticArraysCore", "Statistics", "TruncatedStacktraces"] -git-tree-sha1 = "615e8358608628b9768275f4bd8c237724e72f08" +deps = ["ArrayInterface", "ConcreteStructs", "DataStructures", "DocStringExtensions", "EnumX", "EnzymeCore", "FastBroadcast", "FastClosures", "FastPower", "FunctionWrappers", "FunctionWrappersWrappers", "LinearAlgebra", "Logging", "Markdown", "MuladdMacro", "Parameters", "PrecompileTools", "Printf", "RecursiveArrayTools", "Reexport", "SciMLBase", "SciMLOperators", "SciMLStructures", "Setfield", "Static", "StaticArraysCore", "Statistics", "SymbolicIndexingInterface", "TruncatedStacktraces"] +git-tree-sha1 = "c1ae1a949a95ee1895e3b48e11982f102152c3aa" uuid = "2b5f629d-d688-5b77-993f-72d75c75574e" -version = "6.164.2" +version = "6.182.0" [deps.DiffEqBase.extensions] DiffEqBaseCUDAExt = "CUDA" @@ -282,6 +288,7 @@ version = "6.164.2" DiffEqBaseMPIExt = "MPI" DiffEqBaseMeasurementsExt = "Measurements" DiffEqBaseMonteCarloMeasurementsExt = "MonteCarloMeasurements" + DiffEqBaseMooncakeExt = "Mooncake" DiffEqBaseReverseDiffExt = "ReverseDiff" DiffEqBaseSparseArraysExt = "SparseArrays" DiffEqBaseTrackerExt = "Tracker" @@ -298,6 +305,7 @@ version = "6.164.2" MPI = "da04e1cc-30fd-572f-bb4f-1f8673147195" Measurements = "eff96d63-e80a-5855-80a2-b1b0885c5ab7" MonteCarloMeasurements = "0987c9cc-fe09-11e8-30f0-b96dd679fdca" + Mooncake = "da2b9cff-9c12-43a0-ae48-6db2b0edb7d6" ReverseDiff = "37e2e3b7-166d-5795-8a7a-e32c996b4267" SparseArrays = "2f01184e-e22b-5df5-ae63-d93ebab69eaf" Tracker = "9f7883ad-71c0-57eb-9f7f-b5c9e6d3789c" @@ -317,9 +325,9 @@ version = "1.15.1" [[deps.DifferentiationInterface]] deps = ["ADTypes", "LinearAlgebra"] -git-tree-sha1 = "479214d2988a837e6d21ac38afdcb03cb2d0994e" +git-tree-sha1 = "c8d85ecfcbaef899308706bebdd8b00107f3fb43" uuid = "a0c0ee7d-e4b9-4e03-894e-1c5f64a51d63" -version = "0.6.43" +version = "0.6.54" [deps.DifferentiationInterface.extensions] DifferentiationInterfaceChainRulesCoreExt = "ChainRulesCore" @@ -329,11 +337,13 @@ version = "0.6.43" DifferentiationInterfaceFiniteDiffExt = "FiniteDiff" DifferentiationInterfaceFiniteDifferencesExt = "FiniteDifferences" DifferentiationInterfaceForwardDiffExt = ["ForwardDiff", "DiffResults"] + DifferentiationInterfaceGPUArraysCoreExt = "GPUArraysCore" DifferentiationInterfaceGTPSAExt = "GTPSA" DifferentiationInterfaceMooncakeExt = "Mooncake" - DifferentiationInterfacePolyesterForwardDiffExt = "PolyesterForwardDiff" + DifferentiationInterfacePolyesterForwardDiffExt = ["PolyesterForwardDiff", "ForwardDiff", "DiffResults"] DifferentiationInterfaceReverseDiffExt = ["ReverseDiff", "DiffResults"] DifferentiationInterfaceSparseArraysExt = "SparseArrays" + DifferentiationInterfaceSparseConnectivityTracerExt = "SparseConnectivityTracer" DifferentiationInterfaceSparseMatrixColoringsExt = "SparseMatrixColorings" DifferentiationInterfaceStaticArraysExt = "StaticArrays" DifferentiationInterfaceSymbolicsExt = "Symbolics" @@ -350,11 +360,13 @@ version = "0.6.43" FiniteDiff = "6a86dc24-6348-571c-b903-95158fe2bd41" FiniteDifferences = "26cc04aa-876d-5657-8c51-4c34ba976000" ForwardDiff = "f6369f11-7733-5829-9624-2563aa707210" + GPUArraysCore = "46192b85-c4d5-4398-a991-12ede77f4527" GTPSA = "b27dd330-f138-47c5-815b-40db9dd9b6e8" Mooncake = "da2b9cff-9c12-43a0-ae48-6db2b0edb7d6" PolyesterForwardDiff = "98d1487c-24ca-40b6-b7ab-df2af84e126b" ReverseDiff = "37e2e3b7-166d-5795-8a7a-e32c996b4267" SparseArrays = "2f01184e-e22b-5df5-ae63-d93ebab69eaf" + SparseConnectivityTracer = "9f842d2f-2579-4b1d-911e-f412cf18a3f5" SparseMatrixColorings = "0a514795-09f3-496d-8182-132a7b665d35" StaticArrays = "90137ffa-7385-5640-81b9-e52037218182" Symbolics = "0c5d862f-8b57-4792-8d23-62f2024744c7" @@ -367,10 +379,9 @@ uuid = "8ba89e20-285c-5b6f-9357-94700520ee1b" version = "1.11.0" [[deps.DocStringExtensions]] -deps = ["LibGit2"] -git-tree-sha1 = "2fb1e02f2b635d0845df5d7c167fec4dd739b00d" +git-tree-sha1 = "7442a5dfe1ebb773c29cc2962a8980f47221d76c" uuid = "ffbed154-4ef7-542d-bbb7-c09d3a79fcae" -version = "0.9.3" +version = "0.9.5" [[deps.Downloads]] deps = ["ArgTools", "FileWatching", "LibCURL", "NetworkOptions"] @@ -378,14 +389,14 @@ uuid = "f43a241f-c20a-4ad4-852c-f6b1247861c6" version = "1.6.0" [[deps.EnumX]] -git-tree-sha1 = "bdb1942cd4c45e3c678fd11569d5cccd80976237" +git-tree-sha1 = "bddad79635af6aec424f53ed8aad5d7555dc6f00" uuid = "4e289a0a-7415-4d19-859d-a7e5c4648b56" -version = "1.0.4" +version = "1.0.5" [[deps.EnzymeCore]] -git-tree-sha1 = "0cdb7af5c39e92d78a0ee8d0a447d32f7593137e" +git-tree-sha1 = "8272a687bca7b5c601c0c24fc0c71bff10aafdfd" uuid = "f151be2c-9106-41f4-ab19-57ee4f262869" -version = "0.8.8" +version = "0.8.12" weakdeps = ["Adapt"] [deps.EnzymeCore.extensions] @@ -413,15 +424,16 @@ uuid = "9aa1b823-49e4-5ca5-8b0f-3971ec8bab6a" version = "0.3.2" [[deps.FastPower]] -git-tree-sha1 = "58c3431137131577a7c379d00fea00be524338fb" +git-tree-sha1 = "5f7afd4b1a3969dc34d692da2ed856047325b06e" uuid = "a4df4552-cc26-4903-aec0-212e50a0e84b" -version = "1.1.1" +version = "1.1.3" [deps.FastPower.extensions] FastPowerEnzymeExt = "Enzyme" FastPowerForwardDiffExt = "ForwardDiff" FastPowerMeasurementsExt = "Measurements" FastPowerMonteCarloMeasurementsExt = "MonteCarloMeasurements" + FastPowerMooncakeExt = "Mooncake" FastPowerReverseDiffExt = "ReverseDiff" FastPowerTrackerExt = "Tracker" @@ -430,6 +442,7 @@ version = "1.1.1" ForwardDiff = "f6369f11-7733-5829-9624-2563aa707210" Measurements = "eff96d63-e80a-5855-80a2-b1b0885c5ab7" MonteCarloMeasurements = "0987c9cc-fe09-11e8-30f0-b96dd679fdca" + Mooncake = "da2b9cff-9c12-43a0-ae48-6db2b0edb7d6" ReverseDiff = "37e2e3b7-166d-5795-8a7a-e32c996b4267" Tracker = "9f7883ad-71c0-57eb-9f7f-b5c9e6d3789c" @@ -479,9 +492,9 @@ version = "0.8.5" [[deps.ForwardDiff]] deps = ["CommonSubexpressions", "DiffResults", "DiffRules", "LinearAlgebra", "LogExpFunctions", "NaNMath", "Preferences", "Printf", "Random", "SpecialFunctions"] -git-tree-sha1 = "a2df1b776752e3f344e5116c06d75a10436ab853" +git-tree-sha1 = "910febccb28d493032495b7009dce7d7f7aee554" uuid = "f6369f11-7733-5829-9624-2563aa707210" -version = "0.10.38" +version = "1.0.1" weakdeps = ["StaticArrays"] [deps.ForwardDiff.extensions] @@ -516,9 +529,9 @@ version = "0.1.1" [[deps.IntelOpenMP_jll]] deps = ["Artifacts", "JLLWrappers", "LazyArtifacts", "Libdl"] -git-tree-sha1 = "0f14a5456bdc6b9731a5682f439a672750a09e48" +git-tree-sha1 = "ec1debd61c300961f98064cfb21287613ad7f303" uuid = "1d5cc7b8-4909-519e-a0f8-d0f5ad9712d0" -version = "2025.0.4+0" +version = "2025.2.0+0" [[deps.InteractiveUtils]] deps = ["Markdown"] @@ -527,14 +540,16 @@ version = "1.11.0" [[deps.Interpolations]] deps = ["Adapt", "AxisAlgorithms", "ChainRulesCore", "LinearAlgebra", "OffsetArrays", "Random", "Ratios", "Requires", "SharedArrays", "SparseArrays", "StaticArrays", "WoodburyMatrices"] -git-tree-sha1 = "88a101217d7cb38a7b481ccd50d21876e1d1b0e0" +git-tree-sha1 = "f2905febca224eade352a573e129ef43aa593354" uuid = "a98d9a8b-a2ab-59e6-89dd-64a1c18fca59" -version = "0.15.1" +version = "0.16.1" [deps.Interpolations.extensions] + InterpolationsForwardDiffExt = "ForwardDiff" InterpolationsUnitfulExt = "Unitful" [deps.Interpolations.weakdeps] + ForwardDiff = "f6369f11-7733-5829-9624-2563aa707210" Unitful = "1986cc42-f94f-5a68-af5c-568840ba703d" [[deps.InverseFunctions]] @@ -562,9 +577,9 @@ version = "1.0.0" [[deps.JLLWrappers]] deps = ["Artifacts", "Preferences"] -git-tree-sha1 = "a007feb38b422fbdab534406aeca1b86823cb4d6" +git-tree-sha1 = "0533e564aae234aff59ab625543145446d8b6ec2" uuid = "692b3bcd-3c85-4b1f-b108-f13ce0eb3210" -version = "1.7.0" +version = "1.7.1" [[deps.Jieko]] deps = ["ExproniconLite"] @@ -574,9 +589,9 @@ version = "0.2.1" [[deps.Krylov]] deps = ["LinearAlgebra", "Printf", "SparseArrays"] -git-tree-sha1 = "b29d37ce30fa401a4563b18880ab91f979a29734" +git-tree-sha1 = "b94257a1a8737099ca40bc7271a8b374033473ed" uuid = "ba0b0d4f-ebba-5204-a429-3ac8c609bfb7" -version = "0.9.10" +version = "0.10.1" [[deps.LaTeXStrings]] git-tree-sha1 = "dda21b8cbd6a6c40d9d02a73230f9d70fed6918c" @@ -591,9 +606,9 @@ version = "0.1.17" [[deps.LazyArrays]] deps = ["ArrayLayouts", "FillArrays", "LinearAlgebra", "MacroTools", "SparseArrays"] -git-tree-sha1 = "866ce84b15e54d758c11946aacd4e5df0e60b7a3" +git-tree-sha1 = "76627adb8c542c6b73f68d4bfd0aa71c9893a079" uuid = "5078a376-72f3-5289-bfd5-ec5146d43c02" -version = "2.6.1" +version = "2.6.2" [deps.LazyArrays.extensions] LazyArraysBandedMatricesExt = "BandedMatrices" @@ -641,6 +656,12 @@ version = "1.11.0+1" uuid = "8f399da3-3557-5675-b5ff-fb832c97cbdb" version = "1.11.0" +[[deps.Libiconv_jll]] +deps = ["Artifacts", "JLLWrappers", "Libdl"] +git-tree-sha1 = "be484f5c92fad0bd8acfef35fe017900b0b73809" +uuid = "94ce4f54-9a6c-5748-9c1c-f9c7231a4531" +version = "1.18.0+0" + [[deps.LineSearch]] deps = ["ADTypes", "CommonSolve", "ConcreteStructs", "FastClosures", "LinearAlgebra", "MaybeInplace", "SciMLBase", "SciMLJacobianOperators", "StaticArraysCore"] git-tree-sha1 = "97d502765cc5cf3a722120f50da03c2474efce04" @@ -660,18 +681,21 @@ version = "1.11.0" [[deps.LinearSolve]] deps = ["ArrayInterface", "ChainRulesCore", "ConcreteStructs", "DocStringExtensions", "EnumX", "GPUArraysCore", "InteractiveUtils", "Krylov", "LazyArrays", "Libdl", "LinearAlgebra", "MKL_jll", "Markdown", "PrecompileTools", "Preferences", "RecursiveArrayTools", "Reexport", "SciMLBase", "SciMLOperators", "Setfield", "StaticArraysCore", "UnPack"] -git-tree-sha1 = "6e975dea0fc1825ef3bc83c11281fdf745a69a43" +git-tree-sha1 = "4a7614717945ce05d1693192f399e3b258c60636" uuid = "7ed4a6bd-45f5-4d41-b270-4a48e9bafcae" -version = "3.4.0" +version = "3.25.1" [deps.LinearSolve.extensions] + LinearSolveBLISExt = ["blis_jll", "LAPACK_jll"] LinearSolveBandedMatricesExt = "BandedMatrices" LinearSolveBlockDiagonalsExt = "BlockDiagonals" LinearSolveCUDAExt = "CUDA" LinearSolveCUDSSExt = "CUDSS" + LinearSolveCUSOLVERRFExt = ["CUSOLVERRF", "SparseArrays"] LinearSolveEnzymeExt = "EnzymeCore" LinearSolveFastAlmostBandedMatricesExt = "FastAlmostBandedMatrices" LinearSolveFastLapackInterfaceExt = "FastLapackInterface" + LinearSolveForwardDiffExt = "ForwardDiff" LinearSolveHYPREExt = "HYPRE" LinearSolveIterativeSolversExt = "IterativeSolvers" LinearSolveKernelAbstractionsExt = "KernelAbstractions" @@ -687,18 +711,22 @@ version = "3.4.0" BlockDiagonals = "0a1fb500-61f7-11e9-3c65-f5ef3456f9f0" CUDA = "052768ef-5323-5732-b1bb-66c8b64840ba" CUDSS = "45b445bb-4962-46a0-9369-b4df9d0f772e" + CUSOLVERRF = "a8cc9031-bad2-4722-94f5-40deabb4245c" EnzymeCore = "f151be2c-9106-41f4-ab19-57ee4f262869" FastAlmostBandedMatrices = "9d29842c-ecb8-4973-b1e9-a27b1157504e" FastLapackInterface = "29a986be-02c6-4525-aec4-84b980013641" + ForwardDiff = "f6369f11-7733-5829-9624-2563aa707210" HYPRE = "b5ffcf37-a2bd-41ab-a3da-4bd9bc8ad771" IterativeSolvers = "42fd0dbc-a981-5370-80f2-aaf504508153" KernelAbstractions = "63c18a36-062a-441e-b654-da1e3ab1ce7c" KrylovKit = "0b1a1467-8014-51b9-945f-bf0ae24f4b77" + LAPACK_jll = "51474c39-65e3-53ba-86ba-03b1b862ec14" Metal = "dde4c033-4e86-420c-a63e-0dd931031962" Pardiso = "46dd5b70-b6fb-5a00-ae2d-e8fea33afaf2" RecursiveFactorization = "f2c3362d-daeb-58d1-803e-2bc74f2840b4" SparseArrays = "2f01184e-e22b-5df5-ae63-d93ebab69eaf" Sparspak = "e56a9233-b9d6-4f03-8d0f-1825330902ac" + blis_jll = "6136c539-28a5-5bf0-87cc-b183200dce32" [[deps.LogExpFunctions]] deps = ["DocStringExtensions", "IrrationalConstants", "LinearAlgebra"] @@ -722,14 +750,14 @@ version = "1.11.0" [[deps.MKL_jll]] deps = ["Artifacts", "IntelOpenMP_jll", "JLLWrappers", "LazyArtifacts", "Libdl", "oneTBB_jll"] -git-tree-sha1 = "5de60bc6cb3899cd318d80d627560fae2e2d99ae" +git-tree-sha1 = "282cadc186e7b2ae0eeadbd7a4dffed4196ae2aa" uuid = "856f044c-d86e-5d09-b602-aeab76dc8ba7" -version = "2025.0.1+1" +version = "2025.2.0+0" [[deps.MacroTools]] -git-tree-sha1 = "72aebe0b5051e5143a079a4685a46da330a40472" +git-tree-sha1 = "1e0228a030642014fe5cfe68c2c0a818f9e3f522" uuid = "1914dd2f-81c6-5fcd-8719-6d5c9610ff09" -version = "0.5.15" +version = "0.5.16" [[deps.ManualMemory]] git-tree-sha1 = "bcaef4fc7a0cfe2cba636d84cda54b5e4e4ca3cd" @@ -767,9 +795,9 @@ version = "1.11.0" [[deps.Moshi]] deps = ["ExproniconLite", "Jieko"] -git-tree-sha1 = "453de0fc2be3d11b9b93ca4d0fddd91196dcf1ed" +git-tree-sha1 = "53f817d3e84537d84545e0ad749e483412dd6b2a" uuid = "2e0e35c7-a2e4-4343-998d-7ef72827ed2d" -version = "0.3.5" +version = "0.3.7" [[deps.MozillaCACerts_jll]] uuid = "14a3606d-f60d-562e-9121-12d972cd8159" @@ -782,9 +810,9 @@ version = "0.2.4" [[deps.NaNMath]] deps = ["OpenLibm_jll"] -git-tree-sha1 = "cc0a5deefdb12ab3a096f00a6d42133af4560d71" +git-tree-sha1 = "9b8215b1ee9e78a293f99797cd31375471b2bcae" uuid = "77ba4419-2d1f-58cd-9bb1-8ffee604a2e3" -version = "1.1.2" +version = "1.1.3" [[deps.NetworkOptions]] uuid = "ca575930-c2e3-43a9-ace4-1e988b2c1908" @@ -792,9 +820,9 @@ version = "1.2.0" [[deps.NonlinearSolve]] deps = ["ADTypes", "ArrayInterface", "BracketingNonlinearSolve", "CommonSolve", "ConcreteStructs", "DiffEqBase", "DifferentiationInterface", "FastClosures", "FiniteDiff", "ForwardDiff", "LineSearch", "LinearAlgebra", "LinearSolve", "NonlinearSolveBase", "NonlinearSolveFirstOrder", "NonlinearSolveQuasiNewton", "NonlinearSolveSpectralMethods", "PrecompileTools", "Preferences", "Reexport", "SciMLBase", "SimpleNonlinearSolve", "SparseArrays", "SparseMatrixColorings", "StaticArraysCore", "SymbolicIndexingInterface"] -git-tree-sha1 = "95def4e218a6832d158feafb9963be0337ea432c" +git-tree-sha1 = "d2ec18c1e4eccbb70b64be2435fc3b06fbcdc0a1" uuid = "8913a72c-1f9b-4ce2-8d82-65094dcecaec" -version = "4.4.0" +version = "4.10.0" [deps.NonlinearSolve.extensions] NonlinearSolveFastLevenbergMarquardtExt = "FastLevenbergMarquardt" @@ -824,9 +852,9 @@ version = "4.4.0" [[deps.NonlinearSolveBase]] deps = ["ADTypes", "Adapt", "ArrayInterface", "CommonSolve", "Compat", "ConcreteStructs", "DifferentiationInterface", "EnzymeCore", "FastClosures", "LinearAlgebra", "Markdown", "MaybeInplace", "Preferences", "Printf", "RecursiveArrayTools", "SciMLBase", "SciMLJacobianOperators", "SciMLOperators", "StaticArraysCore", "SymbolicIndexingInterface", "TimerOutputs"] -git-tree-sha1 = "8a2437b5ead050301b6a6258f226e5137e511000" +git-tree-sha1 = "1d42a315ba627ca0027d49d0efb44e3d88db24aa" uuid = "be0214bd-f91f-a760-ac4e-3421ce2b2da0" -version = "1.5.0" +version = "1.14.0" [deps.NonlinearSolveBase.extensions] NonlinearSolveBaseBandedMatricesExt = "BandedMatrices" @@ -848,15 +876,15 @@ version = "1.5.0" [[deps.NonlinearSolveFirstOrder]] deps = ["ADTypes", "ArrayInterface", "CommonSolve", "ConcreteStructs", "DiffEqBase", "FiniteDiff", "ForwardDiff", "LineSearch", "LinearAlgebra", "LinearSolve", "MaybeInplace", "NonlinearSolveBase", "PrecompileTools", "Reexport", "SciMLBase", "SciMLJacobianOperators", "Setfield", "StaticArraysCore"] -git-tree-sha1 = "aade7ab02ee4c80ec30dc8a2874fc67155c935f1" +git-tree-sha1 = "3f1198ae5cbf21e84b8251a9e62fa1f888f3e4cb" uuid = "5959db7a-ea39-4486-b5fe-2dd0bf03d60d" -version = "1.3.0" +version = "1.7.0" [[deps.NonlinearSolveQuasiNewton]] deps = ["ArrayInterface", "CommonSolve", "ConcreteStructs", "DiffEqBase", "LinearAlgebra", "LinearSolve", "MaybeInplace", "NonlinearSolveBase", "PrecompileTools", "Reexport", "SciMLBase", "SciMLOperators", "StaticArraysCore"] -git-tree-sha1 = "44a132cb32aeafcb35a6238fd91a2f3f8ff5c5b0" +git-tree-sha1 = "40dfaf1bf74f1f700f81d0002d4dd90999598eb2" uuid = "9a2c21bd-3a47-402d-9113-8faf9a0ee114" -version = "1.2.0" +version = "1.8.0" weakdeps = ["ForwardDiff"] [deps.NonlinearSolveQuasiNewton.extensions] @@ -864,18 +892,18 @@ weakdeps = ["ForwardDiff"] [[deps.NonlinearSolveSpectralMethods]] deps = ["CommonSolve", "ConcreteStructs", "DiffEqBase", "LineSearch", "MaybeInplace", "NonlinearSolveBase", "PrecompileTools", "Reexport", "SciMLBase"] -git-tree-sha1 = "f28b1ab17b5f15eb2b174eaf8813cf17f0b3e6c0" +git-tree-sha1 = "84de5a469e119eb2c22ae07c543dc4e7f7001ee7" uuid = "26075421-4e9a-44e1-8bd1-420ed7ad02b2" -version = "1.1.0" +version = "1.3.0" weakdeps = ["ForwardDiff"] [deps.NonlinearSolveSpectralMethods.extensions] NonlinearSolveSpectralMethodsForwardDiffExt = "ForwardDiff" [[deps.OffsetArrays]] -git-tree-sha1 = "5e1897147d1ff8d98883cda2be2187dcf57d8f0c" +git-tree-sha1 = "117432e406b5c023f665fa73dc26e79ec3630151" uuid = "6fe1bfb0-de20-5000-8ca7-80f57d26f881" -version = "1.15.0" +version = "1.17.0" weakdeps = ["Adapt"] [deps.OffsetArrays.extensions] @@ -889,7 +917,7 @@ version = "0.3.27+1" [[deps.OpenLibm_jll]] deps = ["Artifacts", "Libdl"] uuid = "05823500-19ac-5b8b-9628-191a04bc5112" -version = "0.8.1+4" +version = "0.8.5+0" [[deps.OpenSpecFun_jll]] deps = ["Artifacts", "CompilerSupportLibraries_jll", "JLLWrappers", "Libdl"] @@ -898,9 +926,9 @@ uuid = "efe28fd5-8261-553b-a9e1-b2916fc3738e" version = "0.5.6+0" [[deps.OrderedCollections]] -git-tree-sha1 = "cc4054e898b852042d7b503313f7ad03de99c3dd" +git-tree-sha1 = "05868e21324cede2207c6f0f466b4bfef6d5e7ee" uuid = "bac558e1-5e72-5ebc-8fee-abe8a469f55d" -version = "1.8.0" +version = "1.8.1" [[deps.Parameters]] deps = ["OrderedCollections", "UnPack"] @@ -921,9 +949,9 @@ version = "1.11.0" [[deps.Polyester]] deps = ["ArrayInterface", "BitTwiddlingConvenienceFunctions", "CPUSummary", "IfElse", "ManualMemory", "PolyesterWeave", "Static", "StaticArrayInterface", "StrideArraysCore", "ThreadingUtilities"] -git-tree-sha1 = "6d38fea02d983051776a856b7df75b30cf9a3c1f" +git-tree-sha1 = "6f7cd22a802094d239824c57d94c8e2d0f7cfc7d" uuid = "f517fe37-dbe3-4b94-8317-1923a5111588" -version = "0.7.16" +version = "0.7.18" [[deps.PolyesterWeave]] deps = ["BitTwiddlingConvenienceFunctions", "CPUSummary", "IfElse", "Static", "ThreadingUtilities"] @@ -931,6 +959,20 @@ git-tree-sha1 = "645bed98cd47f72f67316fd42fc47dee771aefcd" uuid = "1d0040c9-8b98-4ee7-8388-3f51789ca0ad" version = "0.2.2" +[[deps.PreallocationTools]] +deps = ["Adapt", "ArrayInterface", "ForwardDiff"] +git-tree-sha1 = "2cc315bb7f6e4d59081bad744cdb911d6374fc7f" +uuid = "d236fae5-4411-538c-8e31-a6e3d9e00b46" +version = "0.4.29" + + [deps.PreallocationTools.extensions] + PreallocationToolsReverseDiffExt = "ReverseDiff" + PreallocationToolsSparseConnectivityTracerExt = "SparseConnectivityTracer" + + [deps.PreallocationTools.weakdeps] + ReverseDiff = "37e2e3b7-166d-5795-8a7a-e32c996b4267" + SparseConnectivityTracer = "9f842d2f-2579-4b1d-911e-f412cf18a3f5" + [[deps.PrecompileTools]] deps = ["Preferences"] git-tree-sha1 = "5aa36f7049a63a1528fe8f7c3f2113413ffd4e1f" @@ -943,6 +985,12 @@ git-tree-sha1 = "9306f6085165d270f7e3db02af26a400d580f5c6" uuid = "21216c6a-2e73-6563-6e65-726566657250" version = "1.4.3" +[[deps.PrettyTables]] +deps = ["Crayons", "LaTeXStrings", "Markdown", "PrecompileTools", "Printf", "Reexport", "StringManipulation", "Tables"] +git-tree-sha1 = "1101cd475833706e4d0e7b122218257178f48f34" +uuid = "08abe8d2-0d0c-5749-adfa-8a2ac140af0d" +version = "2.4.0" + [[deps.Printf]] deps = ["Unicode"] uuid = "de0858da-6303-5e67-8744-51eddeeeb8d7" @@ -971,13 +1019,14 @@ version = "1.3.4" [[deps.RecursiveArrayTools]] deps = ["Adapt", "ArrayInterface", "DocStringExtensions", "GPUArraysCore", "IteratorInterfaceExtensions", "LinearAlgebra", "RecipesBase", "StaticArraysCore", "Statistics", "SymbolicIndexingInterface", "Tables"] -git-tree-sha1 = "e96b644f7bfbf1015f8e42a7c7abfae2a48fafbf" +git-tree-sha1 = "f8726bd5a8b7f5f5d3f6c0ce4793454a599b5243" uuid = "731186ca-8d62-57ce-b412-fbd966d074cd" -version = "3.31.0" +version = "3.36.0" [deps.RecursiveArrayTools.extensions] RecursiveArrayToolsFastBroadcastExt = "FastBroadcast" RecursiveArrayToolsForwardDiffExt = "ForwardDiff" + RecursiveArrayToolsKernelAbstractionsExt = "KernelAbstractions" RecursiveArrayToolsMeasurementsExt = "Measurements" RecursiveArrayToolsMonteCarloMeasurementsExt = "MonteCarloMeasurements" RecursiveArrayToolsReverseDiffExt = ["ReverseDiff", "Zygote"] @@ -989,6 +1038,7 @@ version = "3.31.0" [deps.RecursiveArrayTools.weakdeps] FastBroadcast = "7034ab61-46d4-4ed7-9d0f-46aef9175898" ForwardDiff = "f6369f11-7733-5829-9624-2563aa707210" + KernelAbstractions = "63c18a36-062a-441e-b654-da1e3ab1ce7c" Measurements = "eff96d63-e80a-5855-80a2-b1b0885c5ab7" MonteCarloMeasurements = "0987c9cc-fe09-11e8-30f0-b96dd679fdca" ReverseDiff = "37e2e3b7-166d-5795-8a7a-e32c996b4267" @@ -1010,9 +1060,9 @@ version = "1.3.1" [[deps.RuntimeGeneratedFunctions]] deps = ["ExprTools", "SHA", "Serialization"] -git-tree-sha1 = "04c968137612c4a5629fa531334bb81ad5680f00" +git-tree-sha1 = "86a8a8b783481e1ea6b9c91dd949cb32191f8ab4" uuid = "7e49a35a-f44a-4d26-94aa-eba1b4ca6b47" -version = "0.5.13" +version = "0.5.15" [[deps.SHA]] uuid = "ea8e919c-243c-51af-8825-aaa63cd721ce" @@ -1024,10 +1074,10 @@ uuid = "94e857df-77ce-4151-89e5-788b33177be4" version = "0.1.0" [[deps.SciMLBase]] -deps = ["ADTypes", "Accessors", "ArrayInterface", "CommonSolve", "ConstructionBase", "Distributed", "DocStringExtensions", "EnumX", "FunctionWrappersWrappers", "IteratorInterfaceExtensions", "LinearAlgebra", "Logging", "Markdown", "Moshi", "PrecompileTools", "Preferences", "Printf", "RecipesBase", "RecursiveArrayTools", "Reexport", "RuntimeGeneratedFunctions", "SciMLOperators", "SciMLStructures", "StaticArraysCore", "Statistics", "SymbolicIndexingInterface"] -git-tree-sha1 = "ee305515b0946db5f56af699e8b5804fee04146c" +deps = ["ADTypes", "Accessors", "Adapt", "ArrayInterface", "CommonSolve", "ConstructionBase", "Distributed", "DocStringExtensions", "EnumX", "FunctionWrappersWrappers", "IteratorInterfaceExtensions", "LinearAlgebra", "Logging", "Markdown", "Moshi", "PrecompileTools", "Preferences", "Printf", "RecipesBase", "RecursiveArrayTools", "Reexport", "RuntimeGeneratedFunctions", "SciMLOperators", "SciMLStructures", "StaticArraysCore", "Statistics", "SymbolicIndexingInterface"] +git-tree-sha1 = "c056c723b68700fec386dfde8c577089df720c8e" uuid = "0bca4576-84f4-4d90-8ffe-ffa030f20462" -version = "2.75.1" +version = "2.108.0" [deps.SciMLBase.extensions] SciMLBaseChainRulesCoreExt = "ChainRulesCore" @@ -1037,7 +1087,7 @@ version = "2.75.1" SciMLBasePyCallExt = "PyCall" SciMLBasePythonCallExt = "PythonCall" SciMLBaseRCallExt = "RCall" - SciMLBaseZygoteExt = "Zygote" + SciMLBaseZygoteExt = ["Zygote", "ChainRulesCore"] [deps.SciMLBase.weakdeps] ChainRules = "082447d4-558c-5d27-93f4-14fc19e9eca2" @@ -1052,15 +1102,15 @@ version = "2.75.1" [[deps.SciMLJacobianOperators]] deps = ["ADTypes", "ArrayInterface", "ConcreteStructs", "ConstructionBase", "DifferentiationInterface", "FastClosures", "LinearAlgebra", "SciMLBase", "SciMLOperators"] -git-tree-sha1 = "f66048bb969e67bd7d1bdd03cd0b81219642bbd0" +git-tree-sha1 = "3414071e3458f3065de7fa5aed55283b236b4907" uuid = "19f34311-ddf3-4b8b-af20-060888a46c0e" -version = "0.1.1" +version = "0.1.8" [[deps.SciMLOperators]] deps = ["Accessors", "ArrayInterface", "DocStringExtensions", "LinearAlgebra", "MacroTools"] -git-tree-sha1 = "6149620767866d4b0f0f7028639b6e661b6a1e44" +git-tree-sha1 = "7d3a1519dc4d433a6b20035eaff20bde8be77c66" uuid = "c0aeaf25-5076-4817-a8d5-81caf7dfa961" -version = "0.3.12" +version = "1.4.0" weakdeps = ["SparseArrays", "StaticArraysCore"] [deps.SciMLOperators.extensions] @@ -1090,9 +1140,9 @@ version = "1.11.0" [[deps.SimpleNonlinearSolve]] deps = ["ADTypes", "ArrayInterface", "BracketingNonlinearSolve", "CommonSolve", "ConcreteStructs", "DifferentiationInterface", "FastClosures", "FiniteDiff", "ForwardDiff", "LineSearch", "LinearAlgebra", "MaybeInplace", "NonlinearSolveBase", "PrecompileTools", "Reexport", "SciMLBase", "Setfield", "StaticArraysCore"] -git-tree-sha1 = "a3868a6add9f5989d1f4bd21de0333ef89fb9d9f" +git-tree-sha1 = "09d986e27a606f172c5b6cffbd8b8b2f10bf1c75" uuid = "727e6d20-b764-4bd8-a329-72de5adea6c7" -version = "2.1.0" +version = "2.7.0" [deps.SimpleNonlinearSolve.extensions] SimpleNonlinearSolveChainRulesCoreExt = "ChainRulesCore" @@ -1116,20 +1166,26 @@ uuid = "2f01184e-e22b-5df5-ae63-d93ebab69eaf" version = "1.11.0" [[deps.SparseMatrixColorings]] -deps = ["ADTypes", "DataStructures", "DocStringExtensions", "LinearAlgebra", "Random", "SparseArrays"] -git-tree-sha1 = "e0ae9189392572abe85bc9fd4ce35e772b1e1e10" +deps = ["ADTypes", "DocStringExtensions", "LinearAlgebra", "PrecompileTools", "Random", "SparseArrays"] +git-tree-sha1 = "9de43e0b9b976f1019bf7a879a686c4514520078" uuid = "0a514795-09f3-496d-8182-132a7b665d35" -version = "0.4.14" -weakdeps = ["Colors"] +version = "0.4.21" [deps.SparseMatrixColorings.extensions] + SparseMatrixColoringsCUDAExt = "CUDA" + SparseMatrixColoringsCliqueTreesExt = "CliqueTrees" SparseMatrixColoringsColorsExt = "Colors" + [deps.SparseMatrixColorings.weakdeps] + CUDA = "052768ef-5323-5732-b1bb-66c8b64840ba" + CliqueTrees = "60701a23-6482-424a-84db-faee86b9b1f8" + Colors = "5ae59095-9a9b-59fe-a467-6f913c188581" + [[deps.SpecialFunctions]] deps = ["IrrationalConstants", "LogExpFunctions", "OpenLibm_jll", "OpenSpecFun_jll"] -git-tree-sha1 = "64cca0c26b4f31ba18f13f6c12af7c85f478cfde" +git-tree-sha1 = "41852b8679f78c8d8961eeadc8f62cef861a52e3" uuid = "276daf66-3868-5448-9aa4-cd146d93841b" -version = "2.5.0" +version = "2.5.1" weakdeps = ["ChainRulesCore"] [deps.SpecialFunctions.extensions] @@ -1137,9 +1193,9 @@ weakdeps = ["ChainRulesCore"] [[deps.Static]] deps = ["CommonWorldInvalidations", "IfElse", "PrecompileTools"] -git-tree-sha1 = "87d51a3ee9a4b0d2fe054bdd3fc2436258db2603" +git-tree-sha1 = "f737d444cb0ad07e61b3c1bef8eb91203c321eff" uuid = "aedffcd0-7271-4cad-89d0-dc628f76c6d3" -version = "1.1.1" +version = "1.2.0" [[deps.StaticArrayInterface]] deps = ["ArrayInterface", "Compat", "IfElse", "LinearAlgebra", "PrecompileTools", "Static"] @@ -1154,9 +1210,9 @@ weakdeps = ["OffsetArrays", "StaticArrays"] [[deps.StaticArrays]] deps = ["LinearAlgebra", "PrecompileTools", "Random", "StaticArraysCore"] -git-tree-sha1 = "0feb6b9031bd5c51f9072393eb5ab3efd31bf9e4" +git-tree-sha1 = "cbea8a6bd7bed51b1619658dec70035e07b8502f" uuid = "90137ffa-7385-5640-81b9-e52037218182" -version = "1.9.13" +version = "1.9.14" weakdeps = ["ChainRulesCore", "Statistics"] [deps.StaticArrays.extensions] @@ -1184,16 +1240,33 @@ git-tree-sha1 = "f35f6ab602df8413a50c4a25ca14de821e8605fb" uuid = "7792a7ef-975c-4747-a70f-980b88e8d1da" version = "0.5.7" +[[deps.StringEncodings]] +deps = ["Libiconv_jll"] +git-tree-sha1 = "b765e46ba27ecf6b44faf70df40c57aa3a547dcb" +uuid = "69024149-9ee7-55f6-a4c4-859efe599b68" +version = "0.3.7" + +[[deps.StringManipulation]] +deps = ["PrecompileTools"] +git-tree-sha1 = "725421ae8e530ec29bcbdddbe91ff8053421d023" +uuid = "892a3eda-7b42-436c-8928-eab12a02cf0e" +version = "0.4.1" + +[[deps.StructMapping]] +git-tree-sha1 = "42f7869cc68f9a83e33ce6a3e408c774900a37e3" +uuid = "7c3b921d-20d6-4eba-ad57-605525e86ab2" +version = "0.2.3" + [[deps.SuiteSparse_jll]] deps = ["Artifacts", "Libdl", "libblastrampoline_jll"] uuid = "bea87d4a-7f5b-5778-9afe-8cc45184846c" version = "7.7.0+0" [[deps.SymbolicIndexingInterface]] -deps = ["Accessors", "ArrayInterface", "RuntimeGeneratedFunctions", "StaticArraysCore"] -git-tree-sha1 = "d6c04e26aa1c8f7d144e1a8c47f1c73d3013e289" +deps = ["Accessors", "ArrayInterface", "PrettyTables", "RuntimeGeneratedFunctions", "StaticArraysCore"] +git-tree-sha1 = "59ca6eddaaa9849e7de9fd1153b6faf0b1db7b80" uuid = "2efcf032-c050-4f8e-a9bb-153293bab1f5" -version = "0.3.38" +version = "0.3.42" [[deps.TOML]] deps = ["Dates"] @@ -1208,9 +1281,9 @@ version = "1.0.1" [[deps.Tables]] deps = ["DataAPI", "DataValueInterfaces", "IteratorInterfaceExtensions", "OrderedCollections", "TableTraits"] -git-tree-sha1 = "598cd7c1f68d1e205689b1c2fe65a9f85846f297" +git-tree-sha1 = "f2c1efbc8f3a609aadf318094f8fc5204bdaf344" uuid = "bd369af6-aec1-5ad0-b16a-f7cc5008161c" -version = "1.12.0" +version = "1.12.1" [[deps.Tar]] deps = ["ArgTools", "SHA"] @@ -1219,21 +1292,21 @@ version = "1.10.0" [[deps.TestEnv]] deps = ["Pkg"] -git-tree-sha1 = "2a57e05cb9854e7260c354f1bcdbe5190adba19f" +git-tree-sha1 = "aec63ef091b11d67040b8b35d2dcdfdc4567c4d0" uuid = "1e6cf692-eddd-4d53-88a5-2d735e33781b" -version = "1.102.0" +version = "1.102.2" [[deps.ThreadingUtilities]] deps = ["ManualMemory"] -git-tree-sha1 = "eda08f7e9818eb53661b3deb74e3159460dfbc27" +git-tree-sha1 = "d969183d3d244b6c33796b5ed01ab97328f2db85" uuid = "8290d209-cae3-49c0-8002-c8c24d57dab5" -version = "0.5.2" +version = "0.5.5" [[deps.TimerOutputs]] deps = ["ExprTools", "Printf"] -git-tree-sha1 = "f57facfd1be61c42321765d3551b3df50f7e09f6" +git-tree-sha1 = "3748bd928e68c7c346b52125cf41fff0de6937d0" uuid = "a759f4b9-e2f1-59dc-863e-4aeb61b1ea8f" -version = "0.5.28" +version = "0.5.29" [deps.TimerOutputs.extensions] FlameGraphsExt = "FlameGraphs" @@ -1279,6 +1352,12 @@ git-tree-sha1 = "752ff27037088b747d3138c828ffc0968d2e7766" uuid = "19641d66-a62d-11e8-2441-8f57a969a9c4" version = "0.5.0" +[[deps.YAML]] +deps = ["Base64", "Dates", "Printf", "StringEncodings"] +git-tree-sha1 = "2f58ac39f64b41fb812340347525be3b590cce3b" +uuid = "ddb6d928-2868-570f-bddf-ab3f9cf99eb6" +version = "0.4.14" + [[deps.Zlib_jll]] deps = ["Libdl"] uuid = "83775a58-1f1d-513f-b197-d71354ab007a" From 1510f6b348fdd4979ed78a3fa0c3bbaf7f327f0b Mon Sep 17 00:00:00 2001 From: 1-Bart-1 Date: Thu, 7 Aug 2025 15:21:48 +0200 Subject: [PATCH 21/26] More versions --- Project.toml | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/Project.toml b/Project.toml index 76741e50..7f2dd4db 100644 --- a/Project.toml +++ b/Project.toml @@ -56,7 +56,7 @@ Parameters = "0.12" Pkg = "1" PreallocationTools = "0.4.25" PrecompileTools = "1.2.1" -Random = "1.11.0" +Random = "1.10.0" SciMLBase = "2.77.0" Serialization = "1" StaticArrays = "1" From 90ff624e1be89e69d4cbaf19a8cbcfedaaf9829a Mon Sep 17 00:00:00 2001 From: jellepoland Date: Fri, 8 Aug 2025 11:07:25 +0200 Subject: [PATCH 22/26] #186 test passing without errors/warnings --- examples/bench.jl | 6 +- examples/ram_air_kite.jl | 6 +- src/VortexStepMethod.jl | 9 +- src/yaml_geometry.jl | 257 ++++++------ test/TestSupport.jl | 5 + .../test_body_aerodynamics.jl | 1 - test/body_aerodynamics/test_results.jl | 14 +- test/plotting/test_plotting.jl | 57 ++- test/runtests.jl | 26 +- test/settings/test_settings.jl | 2 - test/solver/test_solver.jl | 2 - test/test_data_utils.jl | 22 + test/yaml_geometry/test_load_polar_data.jl | 126 ++++++ test/yaml_geometry/test_wing_constructor.jl | 267 ++++++++++++ test/yaml_geometry/test_yaml_geometry.jl | 391 +----------------- test/yaml_geometry/wings/complex_wing.yaml | 0 test/yaml_geometry/wings/simple_wing.yaml | 0 17 files changed, 640 insertions(+), 551 deletions(-) create mode 100644 test/TestSupport.jl create mode 100644 test/yaml_geometry/test_load_polar_data.jl create mode 100644 test/yaml_geometry/test_wing_constructor.jl delete mode 100644 test/yaml_geometry/wings/complex_wing.yaml delete mode 100644 test/yaml_geometry/wings/simple_wing.yaml diff --git a/examples/bench.jl b/examples/bench.jl index 371958f2..89544278 100644 --- a/examples/bench.jl +++ b/examples/bench.jl @@ -56,7 +56,11 @@ println("Rectangular wing, solve:") @time solve(vsm_solver, body_aero, nothing) # Create wing geometry -wing = RamAirWing("data/ram_air_kite/ram_air_kite_body.obj", "data/ram_air_kite/ram_air_kite_foil.dat"; prn=false) +wing = RamAirWing( + joinpath("data", "ram_air_kite", "ram_air_kite_body.obj"), + joinpath("data", "ram_air_kite", "ram_air_kite_foil.dat"); + prn=false +) body_aero = BodyAerodynamics([wing]) # Create solvers diff --git a/examples/ram_air_kite.jl b/examples/ram_air_kite.jl index 1aee03ca..f10b8d5b 100644 --- a/examples/ram_air_kite.jl +++ b/examples/ram_air_kite.jl @@ -9,7 +9,11 @@ DEFORM = false LINEARIZE = false # Create wing geometry -wing = RamAirWing("data/ram_air_kite/ram_air_kite_body.obj", "data/ram_air_kite/ram_air_kite_foil.dat"; prn=PRN) +wing = RamAirWing( + joinpath("data", "ram_air_kite", "ram_air_kite_body.obj"), + joinpath("data", "ram_air_kite", "ram_air_kite_foil.dat"); + prn=PRN +) body_aero = BodyAerodynamics([wing];) println("First init") @time VortexStepMethod.reinit!(body_aero) diff --git a/src/VortexStepMethod.jl b/src/VortexStepMethod.jl index 5d8b1918..c852c48e 100644 --- a/src/VortexStepMethod.jl +++ b/src/VortexStepMethod.jl @@ -40,6 +40,7 @@ export PanelDistribution, LINEAR, COSINE, COSINE_VAN_GARREL, SPLIT_PROVIDED, UNC export InitialGammaDistribution, ELLIPTIC, ZEROS export SolverStatus, FEASIBLE, INFEASIBLE, FAILURE export SolverType, LOOP, NONLIN +export load_polar_data export plot_geometry, plot_distribution, plot_circulation_distribution, plot_polars, save_plot, show_plot, plot_polar_data @@ -202,7 +203,9 @@ const AeroData = Union{ } function menu() - Main.include("examples/menu.jl") + # Load the examples menu using a portable path + ex = joinpath(dirname(pathof(@__MODULE__)), "..", "examples", "menu.jl") + Base.include(Main, normpath(ex)) end """ @@ -213,11 +216,11 @@ Copy all example scripts to the folder "examples" """ function copy_examples() PATH = "examples" - if ! isdir(PATH) + if ! isdir(PATH) mkdir(PATH) end src_path = joinpath(dirname(pathof(@__MODULE__)), "..", PATH) - copy_files("examples", readdir(src_path)) + copy_files(PATH, readdir(src_path)) end function install_examples(add_packages=true) diff --git a/src/yaml_geometry.jl b/src/yaml_geometry.jl index 6f395014..e108f9b6 100644 --- a/src/yaml_geometry.jl +++ b/src/yaml_geometry.jl @@ -1,37 +1,9 @@ - - -""" - load_polar_data(csv_file_path) - -Load polar data from a CSV file using only `readlines`. -Expected format: header row and columns alpha, cl, cd, cm (case-insensitive, order arbitrary). -- alpha: Angle of attack in degrees -- cl: Lift coefficient -- cd: Drag coefficient -- cm: Moment coefficient - -Returns (aero_data, POLAR_VECTORS) or (nothing, INVISCID) if missing/invalid. -""" - -# Structs for YAML parsing using StructMapping.jl -@kwdef struct WingAirfoilInfo - csv_file_path::String = "" +# Data structures for YAML wing geometry +@with_kw struct WingAirfoilInfo + csv_file_path::String end -@kwdef struct WingAirfoilData - airfoil_id::Int64 - type::String - info_dict::WingAirfoilInfo -end - -@kwdef struct WingAirfoils - alpha_range::Vector{Float64} - reynolds::Float64 - headers::Vector{String} - data::Vector{WingAirfoilData} -end - -@kwdef struct WingSectionData +@with_kw struct WingSectionData airfoil_id::Int64 LE_x::Float64 LE_y::Float64 @@ -41,115 +13,162 @@ end TE_z::Float64 end -@kwdef struct WingSections - headers::Vector{String} - data::Vector{WingSectionData} +@with_kw struct WingAirfoilData + airfoil_id::Int64 + type::String + info_dict::WingAirfoilInfo end -@kwdef struct WingGeometry - wing_sections::WingSections - wing_airfoils::WingAirfoils -end +""" + load_polar_data(csv_file_path::String) -> Tuple{Union{Nothing, Tuple{Vector{Float64}, Vector{Float64}, Vector{Float64}, Vector{Float64}}}, Symbol} + +Load aerodynamic polar data from a CSV file using only `readlines`. + +The CSV file must contain a header row with columns for `alpha`, `cl`, `cd`, and `cm` (case-insensitive, order arbitrary). Each subsequent row should contain numeric values for these columns. + +# Arguments +- `csv_file_path::String`: Path to the CSV file containing polar data. + +# Returns +- A tuple `(aero_data, model_type)` where: + - `aero_data`: A tuple of vectors `(alpha, cl, cd, cm)` if the file is valid, or `nothing` if invalid or missing. + - `alpha`: Angle of attack in degrees (converted to radians internally). + - `cl`: Lift coefficient. + - `cd`: Drag coefficient. + - `cm`: Moment coefficient. + - `model_type`: `POLAR_VECTORS` if data is loaded, or `INVISCID` if not. + +# Behavior +- If the file is missing, empty, or invalid, a warning is issued and `(nothing, INVISCID)` is returned. +# Example +```julia +# Create a YAML-based wing from configuration file +wing = Wing( + "path/to/wing_config.yaml"; + n_panels=40, + n_groups=4 +) +``` +""" function load_polar_data(csv_file_path::String) - if isempty(csv_file_path) || !isfile(csv_file_path) - @warn "Polar file not found or empty path: $csv_file_path. Using INVISCID model instead." - return nothing, INVISCID + # Return early for empty path + if isempty(csv_file_path) + @warn "Empty CSV file path provided" + return (nothing, INVISCID) end + + # Check if file exists + if !isfile(csv_file_path) + @warn "CSV file not found: $csv_file_path" + return (nothing, INVISCID) + end + try + # Read all lines from the file lines = readlines(csv_file_path) - isempty(lines) && throw(ArgumentError("File is empty")) - header = lowercase.(split(strip(lines[1]), ',')) - - # Create a mapping from column name to index (1-based for Julia arrays) - col_map = Dict(name => i for (i, name) in enumerate(header)) - required = ["alpha", "cl", "cd", "cm"] - missing = filter(x -> !haskey(col_map, x), required) - if !isempty(missing) - @warn "Missing columns $missing in $csv_file_path. Using INVISCID model instead." - return nothing, INVISCID + + # Check if file is empty + if isempty(lines) + @warn "CSV file is empty: $csv_file_path" + return (nothing, INVISCID) end - # Preallocate arrays - n = length(lines) - 1 - alpha = Vector{Float64}(undef, n) - cl = Vector{Float64}(undef, n) - cd = Vector{Float64}(undef, n) - cm = Vector{Float64}(undef, n) + # Parse header - make case insensitive + header_line = strip(lines[1]) + if isempty(header_line) + @warn "CSV file has empty header: $csv_file_path" + return (nothing, INVISCID) + end + # Split header and normalize to lowercase + header_parts = map(strip ∘ lowercase, split(header_line, ',')) + + # Find column indices for required columns + required_cols = ["alpha", "cl", "cd", "cm"] + col_indices = Dict{String, Int}() + + for (i, col_name) in enumerate(header_parts) + if col_name in required_cols + col_indices[col_name] = i + end + end + + # Check if all required columns are present + missing_cols = setdiff(required_cols, keys(col_indices)) + if !isempty(missing_cols) + @warn "CSV file missing required columns: $(join(missing_cols, ", ")) in $csv_file_path" + return (nothing, INVISCID) + end + + # Parse data rows + data_vectors = Dict{String, Vector{Float64}}() + for col in required_cols + data_vectors[col] = Float64[] + end + for line_num in 2:length(lines) + line = strip(lines[line_num]) + isempty(line) && continue # Skip empty lines + + parts = split(line, ',') + if length(parts) != length(header_parts) + @warn "Line $line_num has incorrect number of columns in $csv_file_path" + return (nothing, INVISCID) # Strict: any malformed data rejects the file + end + + try + for col in required_cols + value_str = strip(parts[col_indices[col]]) + value = parse(Float64, value_str) + push!(data_vectors[col], value) + end + catch e + @warn "Failed to parse line $line_num in $csv_file_path: $e" + return (nothing, INVISCID) # Strict: any parsing error rejects the file + end + end - # Read each data line - for (i, line) in enumerate(lines[2:end]) - fields = split(strip(line), ',') - alpha[i] = parse(Float64, fields[col_map["alpha"]]) - cl[i] = parse(Float64, fields[col_map["cl"]]) - cd[i] = parse(Float64, fields[col_map["cd"]]) - cm[i] = parse(Float64, fields[col_map["cm"]]) + # Check if we got any valid data + if isempty(data_vectors["alpha"]) + @warn "No valid data rows found in $csv_file_path" + return (nothing, INVISCID) end - # Converting to radians - alpha = deg2rad.(alpha) + # Convert alpha from degrees to radians and create tuple + alpha_rad = deg2rad.(data_vectors["alpha"]) + aero_data = (alpha_rad, data_vectors["cl"], data_vectors["cd"], data_vectors["cm"]) + + return (aero_data, POLAR_VECTORS) - return (alpha, cl, cd, cm), POLAR_VECTORS catch e - @warn "Error reading polar file $csv_file_path: $e. Using INVISCID model instead." - return nothing, INVISCID + @warn "Error reading CSV file $csv_file_path: $e" + return (nothing, INVISCID) end end - """ - Wing(geometry_file; kwargs...) + # Module: yaml_geometry.jl -Create a wing model from YAML configuration file with CSV polar data. + This module provides functionality for parsing and handling geometry data from YAML files. + It is intended for use within the VortexStepMethod.jl package to facilitate the import, + validation, and manipulation of geometric configurations specified in YAML format. -This constructor builds a complete aerodynamic model by: -1. Loading wing geometry and airfoil configurations from YAML file -2. Loading aerodynamic polars from CSV files specified in the YAML -3. Creating wing sections with appropriate aerodynamic models -4. Setting up panel distribution and geometric properties + Functions and types in this module allow users to: + - Load geometry definitions from YAML files. + - Convert YAML data into Julia-native structures. + - Validate the integrity and consistency of imported geometry data. -# Arguments -- `geometry_file`: Path to YAML file containing wing geometry and airfoil specifications + Typical use cases include reading wing or blade geometry for aerodynamic simulations. -# Keyword Arguments -- `n_panels=20`: Number of aerodynamic panels across wingspan -- `n_groups=4`: Number of control groups -- `spanwise_distribution=LINEAR`: Panel distribution type -- `spanwise_direction=[0.0, 1.0, 0.0]`: Spanwise direction vector -- `remove_nan=true`: Interpolate NaN values in aerodynamic data -- `prn=true`: Print info messages during construction + # Example + ```julia + geometry = load_yaml_geometry("geometry.yaml") + ``` -# Returns -A fully initialized `Wing` instance ready for aerodynamic simulation. - -# Example YAML format -```yaml -wing_sections: - headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] - data: - - [1, 0.0, 10.0, 0.0, 1.0, 10.0, 0.0] - - [2, 0.0, -10.0, 0.0, 1.0, -10.0, 0.0] - -wing_airfoils: - alpha_range: [-10, 31, 0.5] - reynolds: 1e6 - headers: [airfoil_id, type, info_dict] - data: - - [1, polars, {csv_file_path: "polars/1.csv"}] - - [2, polars, {csv_file_path: "polars/2.csv"}] -``` - -# Example -```julia -# Create a YAML-based wing from configuration file -wing = Wing( - "path/to/wing_config.yaml"; - n_panels=40, - n_groups=4 -) -``` + # See Also + - [`YAML`](@ref) + - [`VortexStepMethod`](@ref) """ function Wing( geometry_file::String; @@ -167,7 +186,7 @@ function Wing( # Load YAML file following Uwe's suggestion data = YAML.load_file(geometry_file) - + # Convert YAML data to our struct format # Convert wing sections wing_sections_data = data["wing_sections"] @@ -222,7 +241,9 @@ function Wing( # Load polar data and create section csv_file_path = get(airfoil_csv_map, section.airfoil_id, "") if !isempty(csv_file_path) && !isabspath(csv_file_path) - # Make relative paths relative to YAML file directory + # NOTE: The spanwise direction is currently restricted to [0.0, 1.0, 0.0] (the global Y axis). + # This is required because downstream geometry and panel generation code assumes the spanwise axis is aligned with Y. + # If you need to support arbitrary spanwise directions, refactor the geometry logic accordingly. csv_file_path = joinpath(dirname(geometry_file), csv_file_path) end aero_data, aero_model = load_polar_data(csv_file_path) diff --git a/test/TestSupport.jl b/test/TestSupport.jl new file mode 100644 index 00000000..4b428502 --- /dev/null +++ b/test/TestSupport.jl @@ -0,0 +1,5 @@ +module TestSupport +export suppress_warnings, test_data_path, create_temp_wing_settings, + get_standard_wing_file, get_complete_settings_file +include("test_data_utils.jl") +end \ No newline at end of file diff --git a/test/body_aerodynamics/test_body_aerodynamics.jl b/test/body_aerodynamics/test_body_aerodynamics.jl index c38dd8be..6e2b7b2b 100644 --- a/test/body_aerodynamics/test_body_aerodynamics.jl +++ b/test/body_aerodynamics/test_body_aerodynamics.jl @@ -5,7 +5,6 @@ using Test using Logging include("../utils.jl") -include("../test_data_utils.jl") @testset "Induction Matrix Creation" begin # Setup diff --git a/test/body_aerodynamics/test_results.jl b/test/body_aerodynamics/test_results.jl index c9436043..0ac6d232 100644 --- a/test/body_aerodynamics/test_results.jl +++ b/test/body_aerodynamics/test_results.jl @@ -4,9 +4,19 @@ using LinearAlgebra using Test using Logging -if !@isdefined ram_wing - # Use absolute paths to ensure files are found +# Helper to find the data directory for test files +function _find_ram_data_dir() data_dir = joinpath(dirname(dirname(@__DIR__)), "data", "ram_air_kite") + if isdir(data_dir) + return data_dir + else + # Fallback for case where test is run from different working directory + return joinpath(@__DIR__, "..", "..", "data", "ram_air_kite") + end +end + +if !@isdefined ram_wing_results + data_dir = _find_ram_data_dir() body_path = joinpath(tempdir(), "ram_air_kite_body.obj") foil_path = joinpath(tempdir(), "ram_air_kite_foil.dat") diff --git a/test/plotting/test_plotting.jl b/test/plotting/test_plotting.jl index 8b9b2619..385abcef 100644 --- a/test/plotting/test_plotting.jl +++ b/test/plotting/test_plotting.jl @@ -2,13 +2,33 @@ using VortexStepMethod using ControlPlots using Test -include("../test_data_utils.jl") +# Resolve repo data directory for ram air kite assets +const _ram_data_dir = joinpath(dirname(dirname(@__DIR__)), "data", "ram_air_kite") + +# Helper to robustly delete files on platforms with occasional file locks +safe_rm(path) = begin + if isfile(path) + try + rm(path; force=true) + catch + sleep(0.2) + try + rm(path; force=true) + catch + # last resort, ignore + end + end + end + nothing +end if !@isdefined ram_wing body_path = joinpath(tempdir(), "ram_air_kite_body.obj") foil_path = joinpath(tempdir(), "ram_air_kite_foil.dat") - cp("../data/ram_air_kite/ram_air_kite_body.obj", body_path; force=true) - cp("../data/ram_air_kite/ram_air_kite_foil.dat", foil_path; force=true) + body_src = joinpath(_ram_data_dir, "ram_air_kite_body.obj") + foil_src = joinpath(_ram_data_dir, "ram_air_kite_foil.dat") + cp(body_src, body_path; force=true) + cp(foil_src, foil_path; force=true) ram_wing = RamAirWing(body_path, foil_path; alpha_range=deg2rad.(-1:1), delta_range=deg2rad.(-1:1)) end @@ -49,9 +69,10 @@ plt.ioff() res = plt.plot([1,2,3]) @test fig isa plt.PyPlot.Figure @test res isa Vector{plt.PyObject} - save_plot(fig, "/tmp", "plot") - @test isfile("/tmp/plot.pdf") - rm("/tmp/plot.pdf") + save_dir = tempdir() + save_plot(fig, save_dir, "plot") + @test isfile(joinpath(save_dir, "plot.pdf")) + safe_rm(joinpath(save_dir, "plot.pdf")) show_plot(fig) body_aero = create_body_aero() if Sys.islinux() @@ -59,18 +80,18 @@ plt.ioff() body_aero, "Rectangular_wing_geometry"; data_type=".pdf", - save_path="/tmp", + save_path=save_dir, is_save=true, is_show=false) @test fig isa plt.PyPlot.Figure - @test isfile("/tmp/Rectangular_wing_geometry_angled_view.pdf") - rm("/tmp/Rectangular_wing_geometry_angled_view.pdf") - @test isfile("/tmp/Rectangular_wing_geometry_front_view.pdf") - rm("/tmp/Rectangular_wing_geometry_front_view.pdf") - @test isfile("/tmp/Rectangular_wing_geometry_side_view.pdf") - rm("/tmp/Rectangular_wing_geometry_side_view.pdf") - @test isfile("/tmp/Rectangular_wing_geometry_top_view.pdf") - rm("/tmp/Rectangular_wing_geometry_top_view.pdf") + @test isfile(joinpath(save_dir, "Rectangular_wing_geometry_angled_view.pdf")) + safe_rm(joinpath(save_dir, "Rectangular_wing_geometry_angled_view.pdf")) + @test isfile(joinpath(save_dir, "Rectangular_wing_geometry_front_view.pdf")) + safe_rm(joinpath(save_dir, "Rectangular_wing_geometry_front_view.pdf")) + @test isfile(joinpath(save_dir, "Rectangular_wing_geometry_side_view.pdf")) + safe_rm(joinpath(save_dir, "Rectangular_wing_geometry_side_view.pdf")) + @test isfile(joinpath(save_dir, "Rectangular_wing_geometry_top_view.pdf")) + safe_rm(joinpath(save_dir, "Rectangular_wing_geometry_top_view.pdf")) # Step 5: Initialize the solvers vsm_solver = Solver(body_aero; aerodynamic_model_type=VSM) @@ -103,13 +124,13 @@ plt.ioff() v_a=v_a, title="Rectangular Wing Polars", data_type=".pdf", - save_path="/tmp", + save_path=save_dir, is_save=true, is_show=false ) @test fig isa plt.PyPlot.Figure - @test isfile("/tmp/Rectangular_Wing_Polars.pdf") - rm("/tmp/Rectangular_Wing_Polars.pdf") + @test isfile(joinpath(save_dir, "Rectangular_Wing_Polars.pdf")) + safe_rm(joinpath(save_dir, "Rectangular_Wing_Polars.pdf")) # Step 9: Test polar data plotting body_aero = BodyAerodynamics([ram_wing]) diff --git a/test/runtests.jl b/test/runtests.jl index a6bf254f..6c6f92cd 100644 --- a/test/runtests.jl +++ b/test/runtests.jl @@ -1,24 +1,19 @@ using Test, VortexStepMethod -# TODO fix allocation tests -# and: https://github.com/JuliaArrays/FixedSizeArrays.jl/blob/d17373edf4144a672cd80a062bf24d017f01e42f/.github/workflows/UnitTests.yml +# Make paths robust (avoid cd("..")) +cd(@__DIR__) # ensure we're in test/ no matter how tests are launched +include("TestSupport.jl") +using .TestSupport -# Check if the compilation options allow maximum performance. +println("Running tests...") + +# keep your env check as-is... const build_is_production_build_env_name = "BUILD_IS_PRODUCTION_BUILD" const build_is_production_build = let v = get(ENV, build_is_production_build_env_name, "true") - if v ∉ ("false", "true") - error("unknown value for environment variable $build_is_production_build_env_name: $v") - end - if v == "true" - true - else - false - end + v == "true" || v == "false" || error("unknown value for $build_is_production_build_env_name: $v") + v == "true" end::Bool -cd("..") -println("Running tests...") - @testset verbose = true "Testing VortexStepMethod..." begin if build_is_production_build include("bench.jl") @@ -38,5 +33,6 @@ println("Running tests...") include("wing_geometry/test_wing_geometry.jl") include("yaml_geometry/test_yaml_geometry.jl") include("Aqua.jl") +end -end \ No newline at end of file +nothing diff --git a/test/settings/test_settings.jl b/test/settings/test_settings.jl index 0d2a3b3c..c7412894 100644 --- a/test/settings/test_settings.jl +++ b/test/settings/test_settings.jl @@ -6,8 +6,6 @@ end using VortexStepMethod using Test -include("../test_data_utils.jl") - @testset "Test settings.jl" begin # Use the absolute path to test data to avoid path concatenation issues project_root = dirname(dirname(@__DIR__)) diff --git a/test/solver/test_solver.jl b/test/solver/test_solver.jl index fecbe852..1d60061a 100644 --- a/test/solver/test_solver.jl +++ b/test/solver/test_solver.jl @@ -2,8 +2,6 @@ using VortexStepMethod using LinearAlgebra using Test -include("../test_data_utils.jl") - @testset "Solver Constructor Tests" begin @testset "Solver Constructor with VSMSettings" begin # Use module-specific test data files diff --git a/test/test_data_utils.jl b/test/test_data_utils.jl index 2b6a4abb..75bcb27b 100644 --- a/test/test_data_utils.jl +++ b/test/test_data_utils.jl @@ -3,6 +3,28 @@ using YAML using Random: randstring +using Logging + +""" + suppress_warnings(f) + +Temporarily suppress all warnings while executing function `f`. +Useful for tests that expect and want to ignore certain warnings. + +# Example +```julia +result = suppress_warnings(() -> some_function_that_warns()) +``` +""" +function suppress_warnings(f) + old_logger = global_logger() + try + global_logger(NullLogger()) + return f() + finally + global_logger(old_logger) + end +end """ test_data_path(module_name, relative_path...) diff --git a/test/yaml_geometry/test_load_polar_data.jl b/test/yaml_geometry/test_load_polar_data.jl new file mode 100644 index 00000000..ccb487e1 --- /dev/null +++ b/test/yaml_geometry/test_load_polar_data.jl @@ -0,0 +1,126 @@ +using VortexStepMethod +using VortexStepMethod: load_polar_data +using LinearAlgebra +using Test +using YAML +using Logging + +@testset "load_polar_data Function Tests" begin + # Setup temporary files for testing + test_csv_path = joinpath(tempdir(), "test_polar.csv") + + # Clean up function + function cleanup_test_files() + isfile(test_csv_path) && rm(test_csv_path; force=true) + end + + @testset "Valid CSV File" begin + # Create a valid CSV file with polar data + csv_content = """alpha,cl,cd,cm + -10.0,0.1,0.02,-0.01 + -5.0,0.5,0.015,-0.005 + 0.0,1.0,0.01,0.0 + 5.0,1.5,0.015,0.005 + 10.0,1.8,0.025,0.01 + 15.0,1.6,0.05,0.015""" + write(test_csv_path, csv_content) + + aero_data, aero_model = load_polar_data(test_csv_path) + + @test aero_model == POLAR_VECTORS + @test aero_data isa Tuple{Vector{Float64}, Vector{Float64}, Vector{Float64}, Vector{Float64}} + @test length(aero_data) == 4 # alpha, cl, cd, cm + @test length(aero_data[1]) == 6 # 6 data points + + # Test that alpha is converted to radians + @test aero_data[1] ≈ deg2rad.([-10.0, -5.0, 0.0, 5.0, 10.0, 15.0]) + + # Test coefficient values + @test aero_data[2] ≈ [0.1, 0.5, 1.0, 1.5, 1.8, 1.6] # cl + @test aero_data[3] ≈ [0.02, 0.015, 0.01, 0.015, 0.025, 0.05] # cd + @test aero_data[4] ≈ [-0.01, -0.005, 0.0, 0.005, 0.01, 0.015] # cm + end + + @testset "Different Column Order" begin + # Test with different column ordering + csv_content = """cm,alpha,cd,cl + -0.01,-10.0,0.02,0.1 + -0.005,-5.0,0.015,0.5 + 0.0,0.0,0.01,1.0""" + write(test_csv_path, csv_content) + + aero_data, aero_model = load_polar_data(test_csv_path) + + @test aero_model == POLAR_VECTORS + @test aero_data[1] ≈ deg2rad.([-10.0, -5.0, 0.0]) # alpha + @test aero_data[2] ≈ [0.1, 0.5, 1.0] # cl + @test aero_data[3] ≈ [0.02, 0.015, 0.01] # cd + @test aero_data[4] ≈ [-0.01, -0.005, 0.0] # cm + end + + @testset "Case Insensitive Headers" begin + # Test with mixed case headers + csv_content = """ALPHA,CL,CD,CM + 0.0,1.0,0.01,0.0 + 5.0,1.5,0.015,0.005""" + write(test_csv_path, csv_content) + + aero_data, aero_model = load_polar_data(test_csv_path) + + @test aero_model == POLAR_VECTORS + @test length(aero_data[1]) == 2 + end + + @testset "Missing File" begin + nonexistent_path = joinpath(tempdir(), "nonexistent.csv") + aero_data, aero_model = suppress_warnings(() -> load_polar_data(nonexistent_path)) + + @test aero_model == INVISCID + @test aero_data === nothing + end + + @testset "Empty File Path" begin + aero_data, aero_model = suppress_warnings(() -> load_polar_data("")) + + @test aero_model == INVISCID + @test aero_data === nothing + end + + @testset "Invalid CSV Format" begin + # Missing required columns + csv_content = """alpha,cl + 0.0,1.0 + 5.0,1.5""" + write(test_csv_path, csv_content) + + aero_data, aero_model = suppress_warnings(() -> load_polar_data(test_csv_path)) + + @test aero_model == INVISCID + @test aero_data === nothing + end + + @testset "Empty CSV File" begin + write(test_csv_path, "") + + aero_data, aero_model = suppress_warnings(() -> load_polar_data(test_csv_path)) + + @test aero_model == INVISCID + @test aero_data === nothing + end + + @testset "Malformed Data" begin + # Invalid numeric data + csv_content = """alpha,cl,cd,cm + invalid,1.0,0.01,0.0 + 5.0,1.5,0.015,0.005""" + write(test_csv_path, csv_content) + + aero_data, aero_model = suppress_warnings(() -> load_polar_data(test_csv_path)) + + @test aero_model == INVISCID + @test aero_data === nothing + end + + # Cleanup after all tests + cleanup_test_files() +end diff --git a/test/yaml_geometry/test_wing_constructor.jl b/test/yaml_geometry/test_wing_constructor.jl new file mode 100644 index 00000000..b7b30a45 --- /dev/null +++ b/test/yaml_geometry/test_wing_constructor.jl @@ -0,0 +1,267 @@ +using VortexStepMethod +using VortexStepMethod: load_polar_data +using LinearAlgebra +using Test +using YAML +using Logging + +@testset "Wing Constructor Tests" begin + # Setup temporary files for testing + test_yaml_path = joinpath(tempdir(), "test_wing.yaml") + test_polar_dir = joinpath(tempdir(), "polars") + + # Clean up function + function cleanup_test_files() + test_dir = dirname(test_yaml_path) + for file in [test_yaml_path, + joinpath(test_dir, "standard_airfoil.csv"), + joinpath(test_dir, "alternate_airfoil.csv")] + isfile(file) && rm(file; force=true) + end + isdir(test_polar_dir) && rm(test_polar_dir; recursive=true, force=true) + end + + # Create polar data directory and files + mkpath(test_polar_dir) + + # Copy the actual polar files to the temp directory for tests that reference them + cp(test_data_path("yaml_geometry", "standard_airfoil.csv"), joinpath(test_polar_dir, "1.csv"); force=true) + cp(test_data_path("yaml_geometry", "alternate_airfoil.csv"), joinpath(test_polar_dir, "2.csv"); force=true) + + # Also copy them to the test directory itself for direct reference tests + test_dir = dirname(test_yaml_path) + cp(test_data_path("yaml_geometry", "standard_airfoil.csv"), joinpath(test_dir, "standard_airfoil.csv"); force=true) + cp(test_data_path("yaml_geometry", "alternate_airfoil.csv"), joinpath(test_dir, "alternate_airfoil.csv"); force=true) + + @testset "Valid YAML Wing Construction" begin + # Use the actual YAML file from the test data + cp(test_data_path("yaml_geometry", "simple_wing.yaml"), test_yaml_path; force=true) + + wing = Wing(test_yaml_path; n_panels=4, n_groups=2) + + @test wing isa Wing + @test wing.n_panels == 4 + @test wing.n_groups == 2 + @test wing.spanwise_distribution == LINEAR + @test wing.spanwise_direction ≈ [0.0, 1.0, 0.0] + @test length(wing.sections) == 2 # simple_wing has 2 sections + + # Test section coordinates (sections are sorted by spanwise position) + # simple_wing.yaml has: [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] and [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] + # Sorted by y-coordinate: y=1.0, y=-1.0 + @test wing.sections[1].LE_point ≈ [0.0, 1.0, 0.0] + @test wing.sections[1].TE_point ≈ [1.0, 1.0, 0.0] + @test wing.sections[2].LE_point ≈ [0.0, -1.0, 0.0] + @test wing.sections[2].TE_point ≈ [1.0, -1.0, 0.0] + + # Test that sections have polar data + @test wing.sections[1].aero_model == POLAR_VECTORS + @test wing.sections[2].aero_model == POLAR_VECTORS + + # Test polar data is loaded + @test wing.sections[1].aero_data isa Tuple + @test length(wing.sections[1].aero_data) == 4 + @test length(wing.sections[1].aero_data[1]) >= 3 # at least 3 alpha points + end + + @testset "Wing Constructor Parameters" begin + # Use the simple_wing.yaml and test custom parameters + cp(test_data_path("yaml_geometry", "simple_wing.yaml"), test_yaml_path; force=true) + + # Test custom parameters + wing = Wing( + test_yaml_path; + n_panels=8, + n_groups=4, + spanwise_distribution=COSINE, + remove_nan=false + ) + + @test wing.n_panels == 8 + @test wing.n_groups == 4 + @test wing.spanwise_distribution == COSINE + @test !wing.remove_nan + end + + @testset "Missing Polar Files" begin + # Create YAML with non-existent polar files + yaml_content = """ +wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] + +wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "nonexistent.csv"}] +""" + write(test_yaml_path, yaml_content) + + wing = suppress_warnings(() -> Wing(test_yaml_path; n_panels=2)) + + # Should fall back to INVISCID model + @test wing.sections[1].aero_model == INVISCID + @test wing.sections[1].aero_data === nothing + end + + @testset "Sections Without Polar Files" begin + # Create YAML with empty polar file paths + yaml_content = """ +wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] + +wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: ""}] +""" + write(test_yaml_path, yaml_content) + + wing = suppress_warnings(() -> Wing(test_yaml_path; n_panels=2)) + + # Should fall back to INVISCID model + @test wing.sections[1].aero_model == INVISCID + end + + @testset "Invalid Parameters" begin + yaml_content = """ +wing_sections: + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] + - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] + +wing_airfoils: + alpha_range: [-10, 10, 1] + reynolds: 1000000 + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, {csv_file_path: "polars/1.csv"}] +""" + write(test_yaml_path, yaml_content) + + # Test invalid n_panels/n_groups combination + @test_throws ArgumentError Wing(test_yaml_path; n_panels=5, n_groups=2) + + # Test invalid spanwise direction + @test_throws ArgumentError Wing(test_yaml_path; spanwise_direction=[1.0, 0.0, 0.0]) + end + + @testset "Relative Path Resolution" begin + # Test that relative paths in CSV files are resolved relative to YAML file + subdir = joinpath(tempdir(), "subtest") + mkpath(subdir) + + # Copy the simple wing file to subdirectory + subdir_yaml_path = joinpath(subdir, "wing.yaml") + cp(test_data_path("yaml_geometry", "simple_wing.yaml"), subdir_yaml_path; force=true) + + # Copy the polar file to subdirectory too + subdir_polar_path = joinpath(subdir, "standard_airfoil.csv") + cp(test_data_path("yaml_geometry", "standard_airfoil.csv"), subdir_polar_path; force=true) + + wing = Wing(subdir_yaml_path; n_panels=2) + + # Should successfully load polar data with relative path + @test wing.sections[1].aero_model == POLAR_VECTORS + @test wing.sections[1].aero_data isa Tuple + @test wing.sections[2].aero_model == POLAR_VECTORS + @test wing.sections[2].aero_data isa Tuple + + # Cleanup + rm(subdir; recursive=true) + end + + @testset "Complex Wing Geometry" begin + # Use the actual complex_wing.yaml file + cp(test_data_path("yaml_geometry", "complex_wing.yaml"), test_yaml_path; force=true) + + wing = Wing(test_yaml_path; n_panels=12, n_groups=3) + + @test wing.n_panels == 12 + @test wing.n_groups == 3 + @test length(wing.sections) == 7 + + # Test that different airfoil_ids get different polar data + @test wing.sections[1].aero_model == POLAR_VECTORS + @test wing.sections[2].aero_model == POLAR_VECTORS + + # Verify geometric progression along wingspan + @test wing.sections[1].LE_point[2] == 5.0 # First section at y=5 + @test wing.sections[4].LE_point[2] == 0.0 # Middle section at y=0 + @test wing.sections[7].LE_point[2] == -5.0 # Last section at y=-5 + end + + @testset "VSMSettings Constructor" begin + # Test Wing constructor that takes VSMSettings + # Use the actual simple_wing.yaml file + simple_wing_file = test_data_path("yaml_geometry", "simple_wing.yaml") + + # Create VSMSettings with wing configuration + settings = VSMSettings() + settings.wings = [WingSettings( + geometry_file=simple_wing_file, + n_panels=6, + n_groups=3, + spanwise_panel_distribution=COSINE + )] + + # Test Wing constructor with VSMSettings + wing = Wing(settings) + + @test wing isa Wing + @test wing.n_panels == 6 + @test wing.n_groups == 3 + @test wing.spanwise_distribution == COSINE + @test length(wing.sections) == 2 + @test wing.sections[1].aero_model == POLAR_VECTORS + @test wing.sections[2].aero_model == POLAR_VECTORS + end + + @testset "Shared Test Data Usage" begin + # Demonstrate using module-specific test data files + simple_wing_file = test_data_path("yaml_geometry", "simple_wing.yaml") + @test isfile(simple_wing_file) + + # Test basic Wing construction with shared data + wing = Wing(simple_wing_file; n_panels=4, n_groups=2) + @test wing isa Wing + @test wing.n_panels == 4 + @test wing.n_groups == 2 + @test length(wing.sections) == 2 + + # Test complex wing construction + complex_wing_file = test_data_path("yaml_geometry", "complex_wing.yaml") + @test isfile(complex_wing_file) + + complex_wing = Wing(complex_wing_file; n_panels=12, n_groups=3) + @test complex_wing isa Wing + @test complex_wing.n_panels == 12 + @test complex_wing.n_groups == 3 + @test length(complex_wing.sections) == 7 + + # Verify polar data is loaded from shared files + @test complex_wing.sections[1].aero_model == POLAR_VECTORS + @test complex_wing.sections[1].aero_data isa Tuple + + # Test with module-specific convenience function - create a standard wing for this test + standard_wing_file = simple_wing_file # Use simple_wing as our "standard" + @test isfile(standard_wing_file) + + standard_wing = Wing(standard_wing_file; n_panels=2, n_groups=1) + @test standard_wing isa Wing + @test length(standard_wing.sections) == 2 + end + + # Cleanup after all tests + cleanup_test_files() +end diff --git a/test/yaml_geometry/test_yaml_geometry.jl b/test/yaml_geometry/test_yaml_geometry.jl index fdc9429b..12daa54f 100644 --- a/test/yaml_geometry/test_yaml_geometry.jl +++ b/test/yaml_geometry/test_yaml_geometry.jl @@ -1,392 +1,7 @@ -using VortexStepMethod -using VortexStepMethod: load_polar_data -using LinearAlgebra using Test -using YAML -using Logging - -include("../test_data_utils.jl") - -# Helper function to suppress expected warnings during tests -function suppress_warnings(f) - old_logger = global_logger() - try - global_logger(NullLogger()) - return f() - finally - global_logger(old_logger) - end -end @testset "YAML Geometry Tests" begin - # Setup temporary files for testing - test_csv_path = joinpath(tempdir(), "test_polar.csv") - test_yaml_path = joinpath(tempdir(), "test_wing.yaml") - test_polar_dir = joinpath(tempdir(), "polars") - - # Clean up function - function cleanup_test_files() - test_dir = dirname(test_yaml_path) - for file in [test_csv_path, test_yaml_path, - joinpath(test_dir, "standard_airfoil.csv"), - joinpath(test_dir, "alternate_airfoil.csv")] - isfile(file) && rm(file; force=true) - end - isdir(test_polar_dir) && rm(test_polar_dir; recursive=true, force=true) - end - - @testset "load_polar_data Function Tests" begin - @testset "Valid CSV File" begin - # Create a valid CSV file with polar data - csv_content = """alpha,cl,cd,cm - -10.0,0.1,0.02,-0.01 - -5.0,0.5,0.015,-0.005 - 0.0,1.0,0.01,0.0 - 5.0,1.5,0.015,0.005 - 10.0,1.8,0.025,0.01 - 15.0,1.6,0.05,0.015""" - write(test_csv_path, csv_content) - - aero_data, aero_model = load_polar_data(test_csv_path) - - @test aero_model == POLAR_VECTORS - @test aero_data isa Tuple{Vector{Float64}, Vector{Float64}, Vector{Float64}, Vector{Float64}} - @test length(aero_data) == 4 # alpha, cl, cd, cm - @test length(aero_data[1]) == 6 # 6 data points - - # Test that alpha is converted to radians - @test aero_data[1] ≈ deg2rad.([-10.0, -5.0, 0.0, 5.0, 10.0, 15.0]) - - # Test coefficient values - @test aero_data[2] ≈ [0.1, 0.5, 1.0, 1.5, 1.8, 1.6] # cl - @test aero_data[3] ≈ [0.02, 0.015, 0.01, 0.015, 0.025, 0.05] # cd - @test aero_data[4] ≈ [-0.01, -0.005, 0.0, 0.005, 0.01, 0.015] # cm - end - - @testset "Different Column Order" begin - # Test with different column ordering - csv_content = """cm,alpha,cd,cl - -0.01,-10.0,0.02,0.1 - -0.005,-5.0,0.015,0.5 - 0.0,0.0,0.01,1.0""" - write(test_csv_path, csv_content) - - aero_data, aero_model = load_polar_data(test_csv_path) - - @test aero_model == POLAR_VECTORS - @test aero_data[1] ≈ deg2rad.([-10.0, -5.0, 0.0]) # alpha - @test aero_data[2] ≈ [0.1, 0.5, 1.0] # cl - @test aero_data[3] ≈ [0.02, 0.015, 0.01] # cd - @test aero_data[4] ≈ [-0.01, -0.005, 0.0] # cm - end - - @testset "Case Insensitive Headers" begin - # Test with mixed case headers - csv_content = """ALPHA,CL,CD,CM - 0.0,1.0,0.01,0.0 - 5.0,1.5,0.015,0.005""" - write(test_csv_path, csv_content) - - aero_data, aero_model = load_polar_data(test_csv_path) - - @test aero_model == POLAR_VECTORS - @test length(aero_data[1]) == 2 - end - - @testset "Missing File" begin - nonexistent_path = joinpath(tempdir(), "nonexistent.csv") - aero_data, aero_model = suppress_warnings(() -> load_polar_data(nonexistent_path)) - - @test aero_model == INVISCID - @test aero_data === nothing - end - - @testset "Empty File Path" begin - aero_data, aero_model = suppress_warnings(() -> load_polar_data("")) - - @test aero_model == INVISCID - @test aero_data === nothing - end - - @testset "Invalid CSV Format" begin - # Missing required columns - csv_content = """alpha,cl - 0.0,1.0 - 5.0,1.5""" - write(test_csv_path, csv_content) - - aero_data, aero_model = suppress_warnings(() -> load_polar_data(test_csv_path)) - - @test aero_model == INVISCID - @test aero_data === nothing - end - - @testset "Empty CSV File" begin - write(test_csv_path, "") - - aero_data, aero_model = suppress_warnings(() -> load_polar_data(test_csv_path)) - - @test aero_model == INVISCID - @test aero_data === nothing - end - - @testset "Malformed Data" begin - # Invalid numeric data - csv_content = """alpha,cl,cd,cm - invalid,1.0,0.01,0.0 - 5.0,1.5,0.015,0.005""" - write(test_csv_path, csv_content) - - aero_data, aero_model = suppress_warnings(() -> load_polar_data(test_csv_path)) - - @test aero_model == INVISCID - @test aero_data === nothing - end - end - - @testset "Wing Constructor Tests" begin - # Create polar data directory and files - mkpath(test_polar_dir) - - # Copy the actual polar files to the temp directory for tests that reference them - cp(test_data_path("yaml_geometry", "standard_airfoil.csv"), joinpath(test_polar_dir, "1.csv"); force=true) - cp(test_data_path("yaml_geometry", "alternate_airfoil.csv"), joinpath(test_polar_dir, "2.csv"); force=true) - - # Also copy them to the test directory itself for direct reference tests - test_dir = dirname(test_yaml_path) - cp(test_data_path("yaml_geometry", "standard_airfoil.csv"), joinpath(test_dir, "standard_airfoil.csv"); force=true) - cp(test_data_path("yaml_geometry", "alternate_airfoil.csv"), joinpath(test_dir, "alternate_airfoil.csv"); force=true) - - @testset "Valid YAML Wing Construction" begin - # Use the actual YAML file from the test data - cp(test_data_path("yaml_geometry", "simple_wing.yaml"), test_yaml_path; force=true) - - wing = Wing(test_yaml_path; n_panels=4, n_groups=2) - - @test wing isa Wing - @test wing.n_panels == 4 - @test wing.n_groups == 2 - @test wing.spanwise_distribution == LINEAR - @test wing.spanwise_direction ≈ [0.0, 1.0, 0.0] - @test length(wing.sections) == 2 # simple_wing has 2 sections - - # Test section coordinates (sections are sorted by spanwise position) - # simple_wing.yaml has: [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] and [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] - # Sorted by y-coordinate: y=1.0, y=-1.0 - @test wing.sections[1].LE_point ≈ [0.0, 1.0, 0.0] - @test wing.sections[1].TE_point ≈ [1.0, 1.0, 0.0] - @test wing.sections[2].LE_point ≈ [0.0, -1.0, 0.0] - @test wing.sections[2].TE_point ≈ [1.0, -1.0, 0.0] - - # Test that sections have polar data - @test wing.sections[1].aero_model == POLAR_VECTORS - @test wing.sections[2].aero_model == POLAR_VECTORS - - # Test polar data is loaded - @test wing.sections[1].aero_data isa Tuple - @test length(wing.sections[1].aero_data) == 4 - @test length(wing.sections[1].aero_data[1]) >= 3 # at least 3 alpha points - end - - @testset "Wing Constructor Parameters" begin - # Use the simple_wing.yaml and test custom parameters - cp(test_data_path("yaml_geometry", "simple_wing.yaml"), test_yaml_path; force=true) - - # Test custom parameters - wing = Wing( - test_yaml_path; - n_panels=8, - n_groups=4, - spanwise_distribution=COSINE, - remove_nan=false - ) - - @test wing.n_panels == 8 - @test wing.n_groups == 4 - @test wing.spanwise_distribution == COSINE - @test !wing.remove_nan - end - - @testset "Missing Polar Files" begin - # Create YAML with non-existent polar files - yaml_content = """ -wing_sections: - headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] - data: - - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] - - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] - -wing_airfoils: - alpha_range: [-10, 10, 1] - reynolds: 1000000 - headers: [airfoil_id, type, info_dict] - data: - - [1, polars, {csv_file_path: "nonexistent.csv"}] -""" - write(test_yaml_path, yaml_content) - - wing = suppress_warnings(() -> Wing(test_yaml_path; n_panels=2)) - - # Should fall back to INVISCID model - @test wing.sections[1].aero_model == INVISCID - @test wing.sections[1].aero_data === nothing - end - - @testset "Sections Without Polar Files" begin - # Create YAML with empty polar file paths - yaml_content = """ -wing_sections: - headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] - data: - - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] - - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] - -wing_airfoils: - alpha_range: [-10, 10, 1] - reynolds: 1000000 - headers: [airfoil_id, type, info_dict] - data: - - [1, polars, {csv_file_path: ""}] -""" - write(test_yaml_path, yaml_content) - - wing = suppress_warnings(() -> Wing(test_yaml_path; n_panels=2)) - - # Should fall back to INVISCID model - @test wing.sections[1].aero_model == INVISCID - end - - @testset "Invalid Parameters" begin - yaml_content = """ -wing_sections: - headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] - data: - - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] - - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0] - -wing_airfoils: - alpha_range: [-10, 10, 1] - reynolds: 1000000 - headers: [airfoil_id, type, info_dict] - data: - - [1, polars, {csv_file_path: "polars/1.csv"}] -""" - write(test_yaml_path, yaml_content) - - # Test invalid n_panels/n_groups combination - @test_throws ArgumentError Wing(test_yaml_path; n_panels=5, n_groups=2) - - # Test invalid spanwise direction - @test_throws ArgumentError Wing(test_yaml_path; spanwise_direction=[1.0, 0.0, 0.0]) - end - - @testset "Relative Path Resolution" begin - # Test that relative paths in CSV files are resolved relative to YAML file - subdir = joinpath(tempdir(), "subtest") - mkpath(subdir) - - # Copy the simple wing file to subdirectory - subdir_yaml_path = joinpath(subdir, "wing.yaml") - cp(test_data_path("yaml_geometry", "simple_wing.yaml"), subdir_yaml_path; force=true) - - # Copy the polar file to subdirectory too - subdir_polar_path = joinpath(subdir, "standard_airfoil.csv") - cp(test_data_path("yaml_geometry", "standard_airfoil.csv"), subdir_polar_path; force=true) - - wing = Wing(subdir_yaml_path; n_panels=2) - - # Should successfully load polar data with relative path - @test wing.sections[1].aero_model == POLAR_VECTORS - @test wing.sections[1].aero_data isa Tuple - @test wing.sections[2].aero_model == POLAR_VECTORS - @test wing.sections[2].aero_data isa Tuple - - # Cleanup - rm(subdir; recursive=true) - end - - @testset "Complex Wing Geometry" begin - # Use the actual complex_wing.yaml file - cp(test_data_path("yaml_geometry", "complex_wing.yaml"), test_yaml_path; force=true) - - wing = Wing(test_yaml_path; n_panels=12, n_groups=3) - - @test wing.n_panels == 12 - @test wing.n_groups == 3 - @test length(wing.sections) == 7 - - # Test that different airfoil_ids get different polar data - @test wing.sections[1].aero_model == POLAR_VECTORS - @test wing.sections[2].aero_model == POLAR_VECTORS - - # Verify geometric progression along wingspan - @test wing.sections[1].LE_point[2] == 5.0 # First section at y=5 - @test wing.sections[4].LE_point[2] == 0.0 # Middle section at y=0 - @test wing.sections[7].LE_point[2] == -5.0 # Last section at y=-5 - end - - @testset "VSMSettings Constructor" begin - # Test Wing constructor that takes VSMSettings - # Use the actual simple_wing.yaml file - simple_wing_file = test_data_path("yaml_geometry", "simple_wing.yaml") - - # Create VSMSettings with wing configuration - settings = VSMSettings() - settings.wings = [WingSettings( - geometry_file=simple_wing_file, - n_panels=6, - n_groups=3, - spanwise_panel_distribution=COSINE - )] - - # Test Wing constructor with VSMSettings - wing = Wing(settings) - - @test wing isa Wing - @test wing.n_panels == 6 - @test wing.n_groups == 3 - @test wing.spanwise_distribution == COSINE - @test length(wing.sections) == 2 - @test wing.sections[1].aero_model == POLAR_VECTORS - @test wing.sections[2].aero_model == POLAR_VECTORS - end - - @testset "Shared Test Data Usage" begin - # Demonstrate using module-specific test data files - simple_wing_file = test_data_path("yaml_geometry", "simple_wing.yaml") - @test isfile(simple_wing_file) - - # Test basic Wing construction with shared data - wing = Wing(simple_wing_file; n_panels=4, n_groups=2) - @test wing isa Wing - @test wing.n_panels == 4 - @test wing.n_groups == 2 - @test length(wing.sections) == 2 - - # Test complex wing construction - complex_wing_file = test_data_path("yaml_geometry", "complex_wing.yaml") - @test isfile(complex_wing_file) - - complex_wing = Wing(complex_wing_file; n_panels=12, n_groups=3) - @test complex_wing isa Wing - @test complex_wing.n_panels == 12 - @test complex_wing.n_groups == 3 - @test length(complex_wing.sections) == 7 - - # Verify polar data is loaded from shared files - @test complex_wing.sections[1].aero_model == POLAR_VECTORS - @test complex_wing.sections[1].aero_data isa Tuple - - # Test with module-specific convenience function - create a standard wing for this test - standard_wing_file = simple_wing_file # Use simple_wing as our "standard" - @test isfile(standard_wing_file) - - standard_wing = Wing(standard_wing_file; n_panels=2, n_groups=1) - @test standard_wing isa Wing - @test length(standard_wing.sections) == 2 - end - end - - # Cleanup after all tests - cleanup_test_files() + # Include specific test files for better organization + include("test_load_polar_data.jl") + include("test_wing_constructor.jl") end diff --git a/test/yaml_geometry/wings/complex_wing.yaml b/test/yaml_geometry/wings/complex_wing.yaml deleted file mode 100644 index e69de29b..00000000 diff --git a/test/yaml_geometry/wings/simple_wing.yaml b/test/yaml_geometry/wings/simple_wing.yaml deleted file mode 100644 index e69de29b..00000000 From 298062d690c8e3748541342f908fe984f5594d88 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Fri, 8 Aug 2025 11:47:00 +0200 Subject: [PATCH 23/26] #186 attempt at resolving windows issues --- .../test_body_aerodynamics.jl | 44 +++------- test/test_data_utils.jl | 86 +++++++++---------- 2 files changed, 57 insertions(+), 73 deletions(-) diff --git a/test/body_aerodynamics/test_body_aerodynamics.jl b/test/body_aerodynamics/test_body_aerodynamics.jl index 6e2b7b2b..c022102f 100644 --- a/test/body_aerodynamics/test_body_aerodynamics.jl +++ b/test/body_aerodynamics/test_body_aerodynamics.jl @@ -414,39 +414,23 @@ end end @testset "set_va! with VSMSettings" begin - # Use module-specific test data files - wing_file = test_data_path("body_aerodynamics", "test_wing.yaml") - settings_file = create_temp_wing_settings("body_aerodynamics", "test_wing.yaml"; alpha=10.0, beta=5.0, wind_speed=15.0) - + settings_file = create_temp_wing_settings("body_aerodynamics", "test_wing.yaml"; + alpha=10.0, beta=5.0, wind_speed=15.0) try - # Test set_va! with VSMSettings - settings = VSMSettings(settings_file) - wing = Wing(settings) - body_aero = BodyAerodynamics([wing]) - - # Set velocity using convenience method + settings = VSMSettings(settings_file) + wing = Wing(settings) + body_aero = BodyAerodynamics([wing]) + set_va!(body_aero, settings) - - # Calculate expected velocity vector - α = deg2rad(10.0) - β = deg2rad(5.0) - wind_speed = 15.0 - expected_va = wind_speed * [ - cos(α)*cos(β), # X_b (forward) - sin(β), # Y_b (right) - sin(α)*cos(β) # Z_b (down) - ] - - # Verify that all panels have the correct velocity - for panel in body_aero.panels - @test panel.va ≈ expected_va atol=1e-10 + + α, β, wind_speed = deg2rad(10.0), deg2rad(5.0), 15.0 + expected_va = wind_speed .* [cos(α)*cos(β), sin(β), sin(α)*cos(β)] + + for p in body_aero.panels + @test p.va ≈ expected_va atol=1e-10 end - - # Verify body_aero._va is set correctly @test body_aero._va ≈ expected_va atol=1e-10 - finally - # Cleanup - rm(settings_file; force=true) + isfile(settings_file) && rm(settings_file; force=true) end -end \ No newline at end of file +end diff --git a/test/test_data_utils.jl b/test/test_data_utils.jl index 75bcb27b..23b54c59 100644 --- a/test/test_data_utils.jl +++ b/test/test_data_utils.jl @@ -65,50 +65,49 @@ settings_file = create_temp_wing_settings("body_aerodynamics", "test_wing.yaml"; rm(settings_file) ``` """ -function create_temp_wing_settings(module_name, wing_file; - name="test_wing", - n_panels=4, - n_groups=2, - spanwise_panel_distribution="COSINE", - spanwise_direction=[0.0, 1.0, 0.0], - remove_nan=true, - aerodynamic_model_type="VSM", - density=1.225, - type_initial_gamma_distribution="ZEROS", - alpha=10.0, - beta=5.0, - wind_speed=15.0) - - # Use wing_file path directly if it's already an absolute path, otherwise construct it - wing_file_path = if isabspath(wing_file) - wing_file - else - test_data_path(module_name, wing_file) - end - - settings_content = """ -wings: - - name: "$name" - geometry_file: "$wing_file_path" - n_panels: $n_panels - n_groups: $n_groups - spanwise_panel_distribution: $spanwise_panel_distribution - spanwise_direction: $spanwise_direction - remove_nan: $remove_nan - -solver_settings: - aerodynamic_model_type: $aerodynamic_model_type - density: $density - type_initial_gamma_distribution: $type_initial_gamma_distribution - -condition: - alpha: $alpha - beta: $beta - wind_speed: $wind_speed -""" - +function create_temp_wing_settings(module_name, wing_file; + name="test_wing", + n_panels=4, + n_groups=2, + spanwise_panel_distribution="COSINE", + spanwise_direction=[0.0, 1.0, 0.0], + remove_nan=true, + aerodynamic_model_type="VSM", + density=1.225, + type_initial_gamma_distribution="ZEROS", + alpha=10.0, + beta=5.0, + wind_speed=15.0, +) + wing_file_path = isabspath(wing_file) ? wing_file : test_data_path(module_name, wing_file) + wing_file_path = replace(normpath(wing_file_path), '\\' => '/') + + doc = Dict( + "wings" => [Dict( + "name" => name, + "geometry_file" => wing_file_path, + "n_panels" => n_panels, + "n_groups" => n_groups, + "spanwise_panel_distribution" => spanwise_panel_distribution, + "spanwise_direction" => spanwise_direction, + "remove_nan" => remove_nan, + )], + "solver_settings" => Dict( + "aerodynamic_model_type" => aerodynamic_model_type, + "density" => density, + "type_initial_gamma_distribution" => type_initial_gamma_distribution, + ), + "condition" => Dict( + "alpha" => alpha, + "beta" => beta, + "wind_speed" => wind_speed, + ), + ) + temp_file = joinpath(tempdir(), "temp_wing_settings_$(randstring(8)).yaml") - write(temp_file, settings_content) + open(temp_file, "w") do io + YAML.write(io, doc) + end return temp_file end @@ -154,3 +153,4 @@ function get_complete_settings_file(module_name) return create_temp_wing_settings(module_name, basename(get_standard_wing_file(module_name))) end end + From 6d2e64ab695daa76c3964034e42cb294e449d8ce Mon Sep 17 00:00:00 2001 From: 1-Bart-1 Date: Fri, 8 Aug 2025 14:42:22 +0200 Subject: [PATCH 24/26] Update docstring --- src/yaml_geometry.jl | 43 +++++++++++++++++++++++++++---------------- 1 file changed, 27 insertions(+), 16 deletions(-) diff --git a/src/yaml_geometry.jl b/src/yaml_geometry.jl index e108f9b6..1abf3118 100644 --- a/src/yaml_geometry.jl +++ b/src/yaml_geometry.jl @@ -148,27 +148,38 @@ function load_polar_data(csv_file_path::String) end """ - # Module: yaml_geometry.jl + Wing(geometry_file::String; n_panels=20, n_groups=1, spanwise_distribution=LINEAR, + spanwise_direction=[0.0, 1.0, 0.0], remove_nan=true, prn=false) - This module provides functionality for parsing and handling geometry data from YAML files. - It is intended for use within the VortexStepMethod.jl package to facilitate the import, - validation, and manipulation of geometric configurations specified in YAML format. +Constructs a `Wing` object from a YAML geometry file. - Functions and types in this module allow users to: - - Load geometry definitions from YAML files. - - Convert YAML data into Julia-native structures. - - Validate the integrity and consistency of imported geometry data. +# Arguments +- `geometry_file::String`: Path to a YAML file describing the wing geometry and airfoils. + +# Keyword Arguments +- `n_panels::Int`: Number of spanwise panels (default: 20). +- `n_groups::Int`: Number of grouped sections across the span (default: 1). Must divide `n_panels`. +- `spanwise_distribution`: Spanwise panel distribution type (default: `LINEAR`). +- `spanwise_direction::Vector{Float64}`: Direction of the spanwise axis (default: `[0.0, 1.0, 0.0]`). Must be the global Y axis. +- `remove_nan::Bool`: Remove NaN values from the geometry (default: `true`). +- `prn::Bool`: Print informational messages during construction (default: `false`). + +# Returns +- `Wing`: A fully constructed and initialized `Wing` object. - Typical use cases include reading wing or blade geometry for aerodynamic simulations. +# Description +This function reads a YAML configuration file to define the geometry and airfoil data for a multi-section wing. +Each section and corresponding airfoil is parsed from the YAML file, polar data is loaded, and each section is added +to the wing. The geometry logic currently assumes the spanwise direction is `[0.0, 1.0, 0.0]` (aligned with the global Y axis). - # Example - ```julia - geometry = load_yaml_geometry("geometry.yaml") - ``` +# Errors +- Throws an `ArgumentError` if `n_panels` is not divisible by `n_groups`. +- Throws an `ArgumentError` if `spanwise_direction` is not `[0.0, 1.0, 0.0]`. - # See Also - - [`YAML`](@ref) - - [`VortexStepMethod`](@ref) +# Example +```julia +wing = Wing("wing_geometry.yaml"; n_panels=30, n_groups=2, prn=true) +``` """ function Wing( geometry_file::String; From 3b1e431050b7d9c07d7a4f579238ec8326c94717 Mon Sep 17 00:00:00 2001 From: 1-Bart-1 Date: Fri, 8 Aug 2025 14:47:27 +0200 Subject: [PATCH 25/26] Remove unused files --- instantiate | 0 resolve | 0 2 files changed, 0 insertions(+), 0 deletions(-) delete mode 100644 instantiate delete mode 100644 resolve diff --git a/instantiate b/instantiate deleted file mode 100644 index e69de29b..00000000 diff --git a/resolve b/resolve deleted file mode 100644 index e69de29b..00000000 From 10e1d5d6f0a63ab08909abd22f396ca9eca402c8 Mon Sep 17 00:00:00 2001 From: jellepoland Date: Fri, 8 Aug 2025 17:57:53 +0200 Subject: [PATCH 26/26] #186 updated NEWS.md --- NEWS.md | 32 ++++++++++++++++++++++++++++++++ 1 file changed, 32 insertions(+) diff --git a/NEWS.md b/NEWS.md index fdab2a30..fac78b4d 100644 --- a/NEWS.md +++ b/NEWS.md @@ -1,3 +1,35 @@ +## VortexStepMethod v2.0.1 2025-08-08 +### Changed +#### 1. Core New Functionality: YAML Geometry Support +- **New file:** `yaml_geometry.jl` (290+ lines) — Complete YAML-based wing geometry loading. +- **New structs:** `WingSectionData`, `WingAirfoilData`, `WingAirfoilInfo` (with `@with_kw` macros). +- **New function:** `load_polar_data()` — Robust CSV polar data loading with error handling. +- **New constructors:** + - `Wing(geometry_file::String)` — Create wings from YAML files. + - `Wing(settings::VSMSettings)` — Create wings from settings. + +#### 2. Enhanced Settings System +- Renamed `vs()` to `VSMSettings()` constructor. +- Added convenience `Solver(body_aero, settings)` constructor. +- Improved settings structure and validation. + +#### 3. Comprehensive Test Infrastructure +- **Split tests:** Reorganized from monolithic files to modular structure (`test/module_name/test_*.jl`). +- **New test module:** `yaml_geometry` with `test_load_polar_data.jl` and `test_wing_constructor.jl`. +- **Test utilities:** `test_data_utils.jl` with shared helper functions. +- **Test data:** Extensive YAML and CSV test files in `data`. + +#### 4. Data and Examples +- **New data sets:** Complete `TUDELFT_V3_KITE` with CFD polars and literature results. +- **Enhanced examples:** Updated examples to use YAML geometry (e.g., `pyramid_model.jl`, `V3_kite.jl`). +- **Real-world configs:** Production-ready YAML geometry files for various kite configurations. + +#### 5. Core Module Improvements +- **Path handling:** Robust file path resolution for relative/absolute paths. +- **Error handling:** Comprehensive validation and graceful fallback to INVISCID mode. +- **Memory management:** Improved file I/O and cleanup in tests. +- **Documentation:** Added comprehensive docstrings and examples. + ## VortexStepMethod v2.0.0 2025-07-11 ### Changed - bump Interpolations to 0.16