Remove unused P

Author: 1-Bart-1

examples/bench.jl

@@ -39,7 +39,6 @@ vel_app = [cos(alpha), 0.0, sin(alpha)] .* v_a
 set_va!(body_aero, vel_app)
 
 # Step 4: Initialize solvers for both LLT and VSM methods
-P = length(body_aero.panels)
 llt_solver = Solver(body_aero; aerodynamic_model_type=LLT)
 vsm_solver = Solver(body_aero; aerodynamic_model_type=VSM)
 

examples/rectangular_wing.jl

@@ -35,7 +35,6 @@ vel_app = [cos(alpha), 0.0, sin(alpha)] .* v_a
 set_va!(body_aero, vel_app, [0, 0, 0.1])
 
 # Step 4: Initialize solvers for both LLT and VSM methods
-P = length(body_aero.panels)
 llt_solver = Solver(body_aero; aerodynamic_model_type=LLT)
 vsm_solver = Solver(body_aero; aerodynamic_model_type=VSM)
 

examples/stall_model.jl

@@ -45,7 +45,6 @@ end
 body_aero = BodyAerodynamics([CAD_wing])
 
 # Create solvers
-P = length(body_aero.panels)
 vsm_solver = Solver(body_aero; 
     aerodynamic_model_type=VSM,
     is_with_artificial_damping=false

test/bench.jl

@@ -67,7 +67,6 @@ using LinearAlgebra
     set_va!(body_aero, vel_app)
 
     # Initialize solvers for both LLT and VSM methods
-    P = length(body_aero.panels)
     solver = Solver(body_aero)
     nonlin_solver = Solver(body_aero; solver_type=NONLIN)
 
@@ -117,8 +116,7 @@ using LinearAlgebra
             z_airf_array[i, :] .= panel.z_airf
         end
 
-        n_angles = 5
-        alphas = collect(range(-deg2rad(10), deg2rad(10), n_angles))
+        alphas = collect(-20:30)
         cls = [2π * α for α in alphas]
         cds = [0.01 + 0.05 * α^2 for α in alphas]
         cms = [-0.1 * α for α in alphas]
@@ -138,7 +136,6 @@ using LinearAlgebra
                     aero_data)
                 body_aero = BodyAerodynamics([wing])
 
-                P = length(body_aero.panels)
                 solver = Solver(body_aero;
                     aerodynamic_model_type=model
                 )

test/test_body_aerodynamics.jl

@@ -308,7 +308,6 @@ end
     set_va!(body_aero, v_a)
 
     # Run analysis
-    P = length(body_aero.panels)
     loop_solver = Solver(body_aero; 
         aerodynamic_model_type=model, 
         core_radius_fraction=core_radius_fraction,

test/test_plotting.jl

@@ -71,7 +71,6 @@ plt.ioff()
         rm("/tmp/Rectangular_wing_geometry_top_view.pdf")
 
         # Step 5: Initialize the solvers
-        P = length(body_aero.panels)
         vsm_solver = Solver(body_aero; aerodynamic_model_type=VSM)
         llt_solver = Solver(body_aero; aerodynamic_model_type=LLT)