Correct width

Author: 1-Bart-1

src/solver.jl

@@ -54,6 +54,7 @@ Struct for storing the solution of the [solve!](@ref) function. Must contain all
     cl_group_array::MVector{G, Float64} = zeros(G)
     cd_group_array::MVector{G, Float64} = zeros(G)
     cm_group_array::MVector{G, Float64} = zeros(G)
+    alpha_group_array::MVector{G, Float64} = zeros(G)
     solver_status::SolverStatus = FAILURE
 end
 
@@ -302,11 +303,13 @@ function solve!(solver::Solver, body_aero::BodyAerodynamics, gamma_distribution=
         cl_group_array = solver.sol.cl_group_array
         cd_group_array = solver.sol.cd_group_array
         cm_group_array = solver.sol.cm_group_array
+        alpha_group_array = solver.sol.alpha_group_array
         group_moment_dist .= 0.0
         group_moment_coeff_dist .= 0.0
         cl_group_array .= 0.0
         cd_group_array .= 0.0
         cm_group_array .= 0.0
+        alpha_group_array .= 0.0
         panel_idx = 1
         group_idx = 1
         for wing in body_aero.wings
@@ -331,6 +334,7 @@ function solve!(solver::Solver, body_aero::BodyAerodynamics, gamma_distribution=
                             cl_group_array[group_idx] += solver.sol.cl_array[panel_idx]
                             cd_group_array[group_idx] += solver.sol.cd_array[panel_idx]
                             cm_group_array[group_idx] += solver.sol.cm_array[panel_idx]
+                            alpha_group_array[group_idx] += solver.sol.alpha_array[panel_idx]
                             # Accumulate geometry for averaging
                             group_panel.x_airf .+= panel.x_airf
                             group_panel.y_airf .+= panel.y_airf
@@ -345,12 +349,12 @@ function solve!(solver::Solver, body_aero::BodyAerodynamics, gamma_distribution=
                         cl_group_array[group_idx] /= panel_count
                         cd_group_array[group_idx] /= panel_count
                         cm_group_array[group_idx] /= panel_count
+                        alpha_group_array[group_idx] /= panel_count
                         group_panel.x_airf ./= panel_count
                         group_panel.y_airf ./= panel_count
                         group_panel.z_airf ./= panel_count
                         group_panel.va ./= panel_count
                         group_panel.chord /= panel_count
-                        group_panel.width /= panel_count
                         group_idx += 1
                     end
                 elseif wing.grouping_method == REFINE
@@ -378,6 +382,7 @@ function solve!(solver::Solver, body_aero::BodyAerodynamics, gamma_distribution=
                         cl_group_array[target_group_idx] += solver.sol.cl_array[panel_idx]
                         cd_group_array[target_group_idx] += solver.sol.cd_array[panel_idx]
                         cm_group_array[target_group_idx] += solver.sol.cm_array[panel_idx]
+                        alpha_group_array[target_group_idx] += solver.sol.alpha_array[panel_idx]
                         # Accumulate geometry
                         group_panel.x_airf .+= panel.x_airf
                         group_panel.y_airf .+= panel.y_airf
@@ -396,6 +401,7 @@ function solve!(solver::Solver, body_aero::BodyAerodynamics, gamma_distribution=
                             cl_group_array[target_group_idx] /= group_panel_counts[i]
                             cd_group_array[target_group_idx] /= group_panel_counts[i]
                             cm_group_array[target_group_idx] /= group_panel_counts[i]
+                            alpha_group_array[target_group_idx] /= group_panel_counts[i]
                             group_panel.x_airf ./= group_panel_counts[i]
                             group_panel.y_airf ./= group_panel_counts[i]
                             group_panel.z_airf ./= group_panel_counts[i]