Fixed multi-wing bug

Author: ufechner7

src/body_aerodynamics.jl

@@ -1045,15 +1045,16 @@ function set_va!(body_aero::BodyAerodynamics, va::AbstractVector, omega=zeros(MV
     if all(iszero, omega)
         va_distribution .= repeat(reshape(va, 1, 3), n_panels)
     else
+        idx = 1
         for wing in body_aero.wings
-            # Get spanwise positions
-            spanwise_positions = [panel.control_point for panel in body_aero.panels]
-            
-            # Calculate velocities for each panel
-            for i in 1:wing.n_panels
-                omega_va = -omega × spanwise_positions[i]
-                va_distribution[i, :] .= omega_va .+ va
+            panel_end = idx + wing.n_panels - 1
+
+            # Calculate velocities for each panel in this wing slice
+            for j in idx:panel_end
+                omega_va = -omega × body_aero.panels[j].control_point
+                va_distribution[j, :] .= omega_va .+ va
             end
+            idx = panel_end + 1
         end
     end
 

test/body_aerodynamics/test_body_aerodynamics.jl

@@ -469,3 +469,29 @@ end
     @test !body_aero.has_distributed_va
     @test body_aero.va ≈ [11.0, 0.0, 0.0]
 end
+
+@testset "set_va! with omega on multi-wing body" begin
+    wing1 = Wing(2; spanwise_distribution=UNCHANGED)
+    add_section!(wing1, [0.0, 0.0, 0.0], [1.0, 0.0, 0.0], INVISCID)
+    add_section!(wing1, [0.0, 1.0, 0.0], [1.0, 1.0, 0.0], INVISCID)
+    add_section!(wing1, [0.0, 2.0, 0.0], [1.0, 2.0, 0.0], INVISCID)
+
+    wing2 = Wing(2; spanwise_distribution=UNCHANGED)
+    add_section!(wing2, [0.0, 10.0, 0.0], [1.0, 10.0, 0.0], INVISCID)
+    add_section!(wing2, [0.0, 11.0, 0.0], [1.0, 11.0, 0.0], INVISCID)
+    add_section!(wing2, [0.0, 12.0, 0.0], [1.0, 12.0, 0.0], INVISCID)
+
+    refine!(wing1)
+    refine!(wing2)
+    body_aero = BodyAerodynamics([wing1, wing2])
+
+    va = [10.0, 0.0, 0.0]
+    omega = [0.0, 0.0, 1.0]
+    set_va!(body_aero, va, omega)
+
+    for panel in body_aero.panels
+        expected_va = va .+ (-omega × panel.control_point)
+        @test panel.va ≈ expected_va atol=1e-12
+    end
+    @test !body_aero.has_distributed_va
+end