add mwe_03.jl

Author: ufechner7

mwes/mwe_03.jl

@@ -0,0 +1,33 @@
+# fix allocations of this array comprehension:
+# y = [panel.control_point[2] for panel in body_aero.panels]
+
+using VortexStepMethod
+
+
+# Step 1: Define wing parameters
+n_panels = 20          # Number of panels
+span = 20.0            # 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_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
+body_aero = BodyAerodynamics([wing])
+
+y = [panel.control_point[2] for panel in body_aero.panels]
+@allocated y = [panel.control_point[2] for panel in body_aero.panels]