Scalarize moment with panel width

Author: 1-Bart-1

src/solver.jl

@@ -266,7 +266,7 @@ function solve!(solver::Solver, body_aero::BodyAerodynamics, gamma_distribution=
 
         # Calculate the moment distribution (moment on each panel)
         arm = (moment_frac - 0.25) * panel.chord
-        moment_distribution[i] = (ftotal_induced_va ⋅ panel.z_airf) * arm + moment[i] * panel.width
+        moment_distribution[i] = ((ftotal_induced_va ⋅ panel.z_airf) * arm + moment[i]) * panel.width
         moment_coefficient_distribution[i] = moment_distribution[i] / (q_inf * projected_area)
     end
 

test/test_body_aerodynamics.jl

@@ -169,8 +169,8 @@ end
     @test sol.force_coefficients[2] ≈ 0.0                   # CFy
     @test sol.force_coefficients[3] ≈ 0.49055973654418716   # CFz
     @test sol.force_coefficients[3] / sol.force_coefficients[1] ≈ sol.aero_force[3] / sol.aero_force[1]
-    @test sol.moment_distribution[1] ≈ -0.026242454074087297
-    @test sol.moment_coefficient_distribution[1] ≈ -8.686587525353832e-6
+    @test sol.moment_distribution[1] ≈ -0.0006683746751654071 atol=1e-10
+    @test sol.moment_coefficient_distribution[1] ≈ -2.212405554436003e-7 atol=1e-10
     @test sol.moment_distribution[1] / sol.moment_distribution[2] ≈ sol.moment_coefficient_distribution[1] / sol.moment_coefficient_distribution[2]
 
     @test sol.solver_status == FEASIBLE