bugfix

Author: ufechner7

examples/bench.jl

@@ -8,21 +8,21 @@ plot = true
 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]
+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)
+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 
+    [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
+    [0.0, -span/2, 0.0],   # Right tip LE
     [chord, -span/2, 0.0], # Right tip TE
     :inviscid)