More tests

Author: ufechner7

src/plotting.jl

@@ -232,7 +232,10 @@ function plot_geometry(wing_aero, title;
         plt.ion()
         fig = create_geometry_plot(wing_aero, title, view_elevation, view_azimuth)
         plt.display(fig)
+    else
+        fig = create_geometry_plot(wing_aero, title, view_elevation, view_azimuth)
     end
+    fig
 end
 
 """

test/test_plotting.jl

@@ -2,6 +2,37 @@ using VortexStepMethod
 using ControlPlots
 using Test
 
+function result_vsm()
+    # Step 1: Define wing parameters
+    n_panels = 20            # Number of panels
+    span = 20.0             # Wing span [m]
+    chord = 1.0             # Chord length [m]
+    Umag = 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_panel_distribution="linear")
+
+    # Add wing sections - defining only tip sections with inviscid airfoil model
+    add_section!(wing, 
+        [0.0, span/2, 0.0],   # Left tip LE 
+        [chord, span/2, 0.0],  # Left tip TE
+        "inviscid")
+    add_section!(wing, 
+        [0.0, -span/2, 0.0],  # Right tip LE
+        [chord, -span/2, 0.0], # Right tip TE
+        "inviscid")
+
+    # Step 3: Initialize aerodynamics
+    wa = WingAerodynamics([wing])
+    # Set inflow conditions
+    vel_app = [cos(alpha), 0.0, sin(alpha)] .* Umag
+    set_va!(wa, (vel_app, 0.0))  # Second parameter is yaw rate
+    wa
+end
+
 plt.ioff()
 @testset "Plotting" begin
     fig = plt.figure(figsize=(14, 14))
@@ -12,5 +43,22 @@ plt.ioff()
     @test isfile("/tmp/plot.pdf")
     rm("/tmp/plot.pdf")
     show_plot(fig)
+    wa = result_vsm()
+    fig = plot_geometry(
+        wa,
+        "Rectangular_wing_geometry";
+        data_type=".pdf",
+        save_path="/tmp",
+        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")
 end
 plt.ion()