Refactoring

Author: ufechner7

src/solver.jl

@@ -45,6 +45,13 @@ function VSMSolution(P)
     VSMSolution{P}()
 end
 
+struct LoopResult
+    converged::Bool
+    gamma_new::Vector{Float64}
+    alpha_array::Vector{Float64}
+    v_a_array::Vector{Float64}
+end
+
 """
     Solver
 
@@ -125,7 +132,7 @@ function solve!(solver::Solver, body_aero::BodyAerodynamics, gamma_distribution=
     log=false, reference_point=zeros(MVec3), moment_frac=0.1)
 
     # calculate intermediate result
-    (converged, body_aero, gamma_new, reference_point, density, aerodynamic_model_type, core_radius_fraction,
+    (converged, body_aero, gamma_new, reference_point, aerodynamic_model_type, core_radius_fraction,
         mu, alpha_array, v_a_array, va_norm_array, va_unit_array, panels,
         is_only_f_and_gamma_output) = solve_base(solver, body_aero, gamma_distribution; log, reference_point)
     if !isnothing(solver.sol.gamma_distribution)
@@ -135,7 +142,6 @@ function solve!(solver::Solver, body_aero::BodyAerodynamics, gamma_distribution=
     end
 
     # Initialize arrays
-    n_panels = length(panels)
     cl_array = solver.sol.cl_array
     cd_array = solver.sol.cd_array
     cm_array = solver.sol.cm_array
@@ -144,6 +150,7 @@ function solve!(solver::Solver, body_aero::BodyAerodynamics, gamma_distribution=
     solver.sol.moment_coefficient_distribution .= 0
     moment_distribution = solver.sol.moment_distribution
     moment_coefficient_distribution = solver.sol.moment_coefficient_distribution
+    density = solver.density
 
     # Calculate coefficients for each panel
     for (i, panel) in enumerate(panels)                                               # zero bytes
@@ -286,7 +293,7 @@ function solve(solver::Solver, body_aero::BodyAerodynamics, gamma_distribution=n
     log=false, reference_point=zeros(MVec3))
     # calculate intermediate result
     converged,
-    body_aero, gamma_new, reference_point, density, aerodynamic_model_type, core_radius_fraction,
+    body_aero, gamma_new, reference_point, aerodynamic_model_type, core_radius_fraction,
     mu, alpha_array, v_a_array, va_norm_array, va_unit_array, panels,
     is_only_f_and_gamma_output = solve_base(solver, body_aero, gamma_distribution; log, reference_point)
 
@@ -295,7 +302,7 @@ function solve(solver::Solver, body_aero::BodyAerodynamics, gamma_distribution=n
         body_aero,
         gamma_new,
         reference_point,
-        density,
+        solver.density,
         aerodynamic_model_type,
         core_radius_fraction,
         mu,
@@ -406,7 +413,6 @@ function solve_base(solver::Solver, body_aero::BodyAerodynamics, gamma_distribut
         body_aero,
         gamma_new,
         reference_point,
-        solver.density,
         solver.aerodynamic_model_type,
         solver.core_radius_fraction,
         solver.mu,