Add enum WingType

Author: ufechner7

docs/src/types.md

@@ -4,6 +4,7 @@ CurrentModule = VortexStepMethod
 ## Enumerations
 ```@docs
 Model
+WingType
 AeroModel
 PanelDistribution
 InitialGammaDistribution

src/VortexStepMethod.jl

@@ -77,6 +77,18 @@ Enumeration of the implemented model types.
 """
 @enum Model VSM LLT
 
+"""
+    WingType `RECTANGULAR` `CURVED` `ELLIPTICAL`
+
+Enumeration of the implemented wing types.
+
+# Elements:
+- RECTANGULAR
+- CURVED
+- ELLIPTICAL
+"""
+@enum WingType  RECTANGULAR CURVED ELLIPTICAL
+
 """
    AeroModel `LEI_AIRFOIL_BREUKELS` `POLAR_VECTORS` `POLAR_MATRICES` `INVISCID`
 

src/body_aerodynamics.jl

@@ -547,7 +547,7 @@ function calculate_results(
     moment = reshape((cm_array .* 0.5 .* density .* v_a_array.^2 .* chord_array), :, 1)
 
     # Calculate alpha corrections based on model type
-    if aerodynamic_model_type === VSM
+    if aerodynamic_model_type  VSM
         update_effective_angle_of_attack!(
             alpha_corrected,
             body_aero,

src/panel.jl

@@ -121,7 +121,7 @@ function init_aero!(
     # Validate aero model consistency
     panel.aero_model = section_1.aero_model
     aero_model_2 = section_2.aero_model
-    if !(panel.aero_model === aero_model_2)
+    if !(panel.aero_model == aero_model_2)
         throw(ArgumentError("Both sections must have the same aero model, not $(panel.aero_model) and $aero_model_2"))
     end
 
@@ -174,7 +174,7 @@ function init_aero!(
             throw(ArgumentError("Polar data in wrong format: $aero_1"))
         end
 
-    elseif !(panel.aero_model === INVISCID)
+    elseif !(panel.aero_model == INVISCID)
         throw(ArgumentError("Unsupported aero model: $(panel.aero_model)"))
     end
 end

src/plotting.jl

@@ -859,7 +859,7 @@ function VortexStepMethod.plot_polar_data(body_aero::BodyAerodynamics;
         is_show = true,
         use_tex = false
         )
-    if body_aero.panels[1].aero_model === POLAR_MATRICES
+    if body_aero.panels[1].aero_model == POLAR_MATRICES
         set_plot_style()
 
         # Create figure with subplots

src/wing_geometry.jl

@@ -161,9 +161,9 @@ Add a new section to the wing.
 """
 function add_section!(wing::Wing, LE_point::Vector{Float64}, 
                      TE_point::Vector{Float64}, aero_model::AeroModel, aero_data::AeroData=nothing)
-    if aero_model === POLAR_VECTORS && wing.remove_nan
+    if aero_model == POLAR_VECTORS && wing.remove_nan
         aero_data = remove_vector_nans(aero_data)
-    elseif aero_model === POLAR_MATRICES && wing.remove_nan
+    elseif aero_model == POLAR_MATRICES && wing.remove_nan
         interpolate_matrix_nans!.(aero_data[3:5])
     end
     push!(wing.sections, Section(LE_point, TE_point, aero_model, aero_data))
@@ -282,7 +282,7 @@ function calculate_new_aero_data(aero_model,
 
     model_type = aero_model[section_index]
     model_type_2 = aero_model[section_index+1]
-    if !(model_type === model_type_2)
+    if !(model_type == model_type_2)
         throw(ArgumentError("Different aero models over the span are not supported"))
     end
 
@@ -326,7 +326,7 @@ function calculate_new_aero_data(aero_model,
             return (alpha_left, delta_left, CL_data, CD_data, CM_data)
         end
 
-    elseif model_type === LEI_AIRFOIL_BREUKELS
+    elseif model_type == LEI_AIRFOIL_BREUKELS
         tube_diameter_left = aero_data[section_index][1]
         tube_diameter_right = aero_data[section_index + 1][1]
         tube_diameter_i = tube_diameter_left * left_weight + tube_diameter_right * right_weight
@@ -462,7 +462,7 @@ function refine_mesh_for_linear_cosine_distribution!(
     end
 
     # Apply van Garrel distribution if requested
-    if spanwise_panel_distribution === :cosine_van_Garrel
+    if spanwise_panel_distribution == COSINE_VAN_GARREL
         idx = calculate_cosine_van_Garrel!(wing, idx)
     end
 

test/test_body_aerodynamics.jl

@@ -253,7 +253,7 @@ end
         @test wing.sections[1].TE_point ≈ [0.0, 0.0, -3.0]
     end
 
-    function create_geometry(; model=VSM, wing_type=:rectangular, plotting=false, N=40)
+    function create_geometry(; model=VSM, wing_type=RECTANGULAR, plotting=false, N=40)
         max_chord = 1.0
         span = 17.0
         AR = span^2 / (π * span * max_chord / 4)
@@ -262,7 +262,7 @@ end
         aoa = 5.7106 * π / 180
         v_a = [cos(aoa), 0.0, sin(aoa)] .* v_a
 
-        coord = if wing_type === :rectangular
+        coord = if wing_type == RECTANGULAR
             theta = range(-0.5, 0.5, length=N)
             beta = range(-2, 2, length=N)
             generate_coordinates_rect_wing(
@@ -273,14 +273,12 @@ end
                 N,
                 "lin"
             )
-        elseif wing_type === :curved
+        elseif wing_type == CURVED
             generate_coordinates_curved_wing(
                 max_chord, span, π/4, 5, N, "cos"
             )
-        elseif wing_type === :elliptical
+        elseif wing_type == ELLIPTICAL
             generate_coordinates_el_wing(max_chord, span, N, "cos")
-        else
-            error("Invalid wing type")
         end
 
         coord_left_to_right = flip_created_coord_in_pairs(deepcopy(coord))
@@ -301,7 +299,7 @@ end
 
     for model in [VSM, LLT]
         @debug "model: $model"
-        for wing_type in [:rectangular, :curved, :elliptical]
+        for wing_type in [RECTANGULAR, CURVED, ELLIPTICAL]
             @debug "wing_type: $wing_type"
             body_aero, coord, v_a, model = create_geometry(
                 model=model, wing_type=wing_type