Feat/xfoil

.gitignore

@@ -1,5 +1,8 @@
 Manifest.toml
 .vscode/settings.json
 venv
+results/TUDELFT_V3_LEI_KITE/polars/$C_L$ vs $C_D$.pdf
+*.bin
 results/TUDELFT_V3_LEI_KITE/polars/tutorial_testing_stall_model_n_panels_54_distribution_split_provided.pdf
 docs/build/
+

Project.toml

@@ -8,14 +8,19 @@ BenchmarkTools = "6e4b80f9-dd63-53aa-95a3-0cdb28fa8baf"
 Colors = "5ae59095-9a9b-59fe-a467-6f913c188581"
 ControlPlots = "23c2ee80-7a9e-4350-b264-8e670f12517c"
 DelimitedFiles = "8bb1440f-4735-579b-a4ab-409b98df4dab"
+Distributed = "8ba89e20-285c-5b6f-9357-94700520ee1b"
 Interpolations = "a98d9a8b-a2ab-59e6-89dd-64a1c18fca59"
 LaTeXStrings = "b964fa9f-0449-5b57-a5c2-d3ea65f4040f"
 LinearAlgebra = "37e2e46d-f89d-539d-b4ee-838fcccc9c8e"
 Logging = "56ddb016-857b-54e1-b83d-db4d58db5568"
 Measures = "442fdcdd-2543-5da2-b0f3-8c86c306513e"
 NonlinearSolve = "8913a72c-1f9b-4ce2-8d82-65094dcecaec"
+Serialization = "9e88b42a-f829-5b0c-bbe9-9e923198166b"
+SharedArrays = "1a1011a3-84de-559e-8e89-a11a2f7dc383"
 StaticArrays = "90137ffa-7385-5640-81b9-e52037218182"
 Statistics = "10745b16-79ce-11e8-11f9-7d13ad32a3b2"
+Timers = "21f18d07-b854-4dab-86f0-c15a3821819a"
+Xfoil = "19641d66-a62d-11e8-2441-8f57a969a9c4"
 
 [compat]
 BenchmarkTools = "1"

data/HL5_ram_air_kite_foil.dat

@@ -0,0 +1,46 @@
+A
+ 1.0000000     0.0000479
+ 0.9666341     0.0017363
+ 0.9038341     0.0066154
+ 0.8342935     0.0136262
+ 0.7624304     0.0214202
+ 0.6907649     0.0299758
+ 0.6203655     0.0397261
+ 0.5500472     0.0504400
+ 0.4788028     0.0614558
+ 0.4074159     0.0732084
+ 0.3368400     0.0848204
+ 0.2692757     0.0941998
+ 0.2083741     0.0988242
+ 0.1573868     0.0983570
+ 0.1169140     0.0924067
+ 0.0828168     0.0826568
+ 0.0560463     0.0704667
+ 0.0361758     0.0577955
+ 0.0215498     0.0452424
+ 0.0115826     0.0329061
+ 0.0055625     0.0219130
+ 0.0019945     0.0124293
+ 0.0002467     0.0035649
+ 0.0004755    -0.0045913
+ 0.0027675    -0.0130849
+ 0.0077900    -0.0220373
+ 0.0162007    -0.0306320
+ 0.0285895    -0.0396469
+ 0.0466671    -0.0494062
+ 0.0728758    -0.0593274
+ 0.1094090    -0.0681156
+ 0.1556860    -0.0747603
+ 0.2093904    -0.0783204
+ 0.2712652    -0.0798598
+ 0.3359510    -0.0788043
+ 0.4038697    -0.0747532
+ 0.4742506    -0.0687364
+ 0.5453696    -0.0615892
+ 0.6158254    -0.0528273
+ 0.6875958    -0.0427482
+ 0.7594140    -0.0320344
+ 0.8304601    -0.0220930
+ 0.9008044    -0.0130373
+ 0.9663063    -0.0044401
+ 1.0000000     0.0000479

examples/ram_air_kite.jl

@@ -4,22 +4,7 @@ using DataFrames
 using LinearAlgebra
 
 # Create wing geometry
-wing = KiteWing("data/HL5_ram_air_kite_body.obj")
-
-alphas = deg2rad.(-10:1:25)  # Range of angles from -10 to 25 degrees
-polars = zeros(length(alphas), 4)  # Matrix for [alpha, CD, CL, CM]
-for (i, alpha) in enumerate(alphas)
-    # Simplified aerodynamic coefficients
-    cd = 0.015 + 0.015 * abs(alpha/10)^1.5  # Drag increases with angle
-    cl = 5.0 * alpha + 0.01 * alpha^2 * exp(-alpha/20)  # Lift with stall behavior
-    cm = -0.02 * alpha  # Linear pitching moment
-
-    polars[i, :] .= [alpha, cd, cl, cm]
-end
-
-for gamma in range(wing.gamma_tip - wing.gamma_tip/10, -wing.gamma_tip + wing.gamma_tip/10, 20)
-    add_section!(wing, gamma, ("polar_data", polars))
-end
+wing = KiteWing("data/HL5_ram_air_kite_body.obj", "data/HL5_ram_air_kite_foil.dat")
 wing_aero = WingAerodynamics([wing])
 
 # Create solvers
@@ -59,34 +44,32 @@ plot_geometry(
 
 # Solving and plotting distributions
 @time results = solve(VSM, wing_aero)
-@time results_with_stall = solve(VSM_with_stall_correction, wing_aero)
+@time results = solve(VSM, wing_aero)
 
 CAD_y_coordinates = [panel.aerodynamic_center[2] for panel in wing_aero.panels]
 
 plot_distribution(
-    [CAD_y_coordinates, CAD_y_coordinates],
-    [results, results_with_stall],
-    ["VSM", "VSM with stall correction"];
+    [CAD_y_coordinates],
+    [results],
+    ["VSM"];
     title="CAD_spanwise_distributions_alpha_$(round(aoa, digits=1))_beta_$(round(side_slip, digits=1))_yaw_$(round(yaw_rate, digits=1))_v_a_$(round(v_a, digits=1))",
     data_type=".pdf",
     is_save=false,
     is_show=true
 )
 
 plot_polars(
-    [VSM, VSM_with_stall_correction],
-    [wing_aero, wing_aero],
+    [VSM],
+    [wing_aero],
     [
-        "VSM CAD 19ribs",
-        "VSM CAD 19ribs , with stall correction",
+        "VSM from Ram Air Kite OBJ and DAT file",
     ];
-    angle_range=range(0, 25, length=25),
+    angle_range=range(0, 20, length=20),
     angle_type="angle_of_attack",
     angle_of_attack=0,
     side_slip=0,
-    yaw_rate=0,
     v_a=10,
-    title="tutorial_testing_stall_model_n_panels_$(wing.n_panels)_distribution_$(wing.spanwise_panel_distribution)",
+    title="ram_kite_panels_$(wing.n_panels)_distribution_$(wing.spanwise_panel_distribution)",
     data_type=".pdf",
     is_save=false,
     is_show=true

examples/stall_model.jl

@@ -111,7 +111,6 @@ plot_polars(
     angle_type="angle_of_attack",
     angle_of_attack=0,
     side_slip=0,
-    yaw_rate=0,
     v_a=10,
     title="tutorial_testing_stall_model_n_panels_$(n_panels)_distribution_$(spanwise_panel_distribution)",
     data_type=".pdf",