Tests pass

Author: 1-Bart-1

src/body_aerodynamics.jl

@@ -110,12 +110,11 @@ function init!(body_aero::BodyAerodynamics;
     idx = 1
     for wing in body_aero.wings
         println("init wing")
-        @time init!(wing; aero_center_location, control_point_location)
-        # @assert false
+        init!(wing; aero_center_location, control_point_location)
         panel_props = wing.panel_props
 
         # Create panels
-        @time for i in 1:wing.n_panels
+        for i in 1:wing.n_panels
             if wing isa RamAirWing
                 delta = wing.delta_dist[i]
             else

src/wing_geometry.jl

@@ -121,14 +121,16 @@ function update_panel_properties!(panel_props::PanelProperties, section_list::Ve
 
     for i in 1:n_panels
         # Define panel points
-        p1 = coords[2i-1, :]     # LE_1
-        p2 = coords[2i+1, :]     # LE_2
-        p3 = coords[2i+2, :]     # TE_2
-        p4 = coords[2i, :]       # TE_1
+        @views begin
+            p1 = coords[2i-1, :]     # LE_1
+            p2 = coords[2i+1, :]     # LE_2
+            p3 = coords[2i+2, :]     # TE_2
+            p4 = coords[2i, :]       # TE_1
+        end
 
         # Calculate control point position
-        di = norm(coords[2i-1, :] * 0.75 + coords[2i, :] * 0.25 - 
-                 (coords[2i+1, :] * 0.75 + coords[2i+2, :] * 0.25))
+        di = norm(coords[2i-1, :] .* 0.75 .+ coords[2i, :] .* 0.25 .- 
+                 (coords[2i+1, :] .* 0.75 .+ coords[2i+2, :] .* 0.25))
 
         ncp = if i == 1
             diplus = norm(coords[2i+1, :] * 0.75 + coords[2i+2, :] * 0.25 -