add bench file

Author: 1-Bart-1

.gitignore

@@ -3,3 +3,4 @@ Manifest.toml
 venv
 results/TUDELFT_V3_LEI_KITE/polars/tutorial_testing_stall_model_n_panels_54_distribution_split_provided.pdf
 docs/build/
+*.bin

src/filament.jl

@@ -57,8 +57,8 @@ function velocity_3D_bound_vortex!(
     elseif norm(r1Xr0) / norm(r0) == 0
         vel .= zeros(3)
     else
-        @info "inside core radius"
-        @info "distance from control point to filament: $(norm(r1Xr0) / norm(r0))"
+        @debug "inside core radius"
+        @debug "distance from control point to filament: $(norm(r1Xr0) / norm(r0))"
 
         # Project onto core radius
         cross3!(r2Xr0, r2, r0)
@@ -71,8 +71,6 @@ function velocity_3D_bound_vortex!(
         vel_ind_proj .= (gamma / (4π)) .* r1_projXr2_proj ./ (norm(r1_projXr2_proj)^2) .* 
                       dot(r0, r1_proj/norm(r1_proj) .- r2_proj/norm(r2_proj))
 
-        @show vel_ind_proj r1_projXr2_proj
-
         vel .= norm(r1Xr0) ./ (norm(r0) * epsilon) .* vel_ind_proj
     end
     nothing

test/bench.jl

@@ -0,0 +1,115 @@
+using BenchmarkTools
+using VortexStepMethod
+using VortexStepMethod: calculate_AIC_matrices, gamma_loop, calculate_results,
+                       update_effective_angle_of_attack_if_VSM, calculate_projected_area,
+                       calculate_cl, calculate_cd_cm,
+                       calculate_velocity_induced_single_ring_semiinfinite,
+                       calculate_velocity_induced_bound_2D,
+                       velocity_3D_bound_vortex!,
+                       velocity_3D_trailing_vortex!,
+                       velocity_3D_trailing_vortex_semiinfinite!,
+                       Panel
+using Test
+using LinearAlgebra
+
+@testset "Function Allocation Tests" begin
+    # Define wing parameters
+    n_panels = 20          # Number of panels
+    span = 20.0            # Wing span [m]
+    chord = 1.0            # Chord length [m]
+    v_a = 20.0            # Magnitude of inflow velocity [m/s]
+    density = 1.225        # Air density [kg/m³]
+    alpha_deg = 30.0       # Angle of attack [degrees]
+    alpha = deg2rad(alpha_deg)
+    
+    # Create test panels
+    panels = []
+    wing = Wing(n_panels, spanwise_panel_distribution="linear")
+    add_section!(wing, 
+        [0.0, span/2, 0.0],   # Left tip LE 
+        [chord, span/2, 0.0],  # Left tip TE
+        "inviscid")
+    add_section!(wing, 
+        [0.0, -span/2, 0.0],  # Right tip LE
+        [chord, -span/2, 0.0], # Right tip TE
+        "inviscid")
+    
+    wing_aero = WingAerodynamics([wing])
+
+    vel_app = [cos(alpha), 0.0, sin(alpha)] .* v_a
+    set_va!(wing_aero, (vel_app, 0.0))  # Second parameter is yaw rate
+
+    # Initialize solvers for both LLT and VSM methods
+    solver = Solver()
+
+    # Pre-allocate arrays
+    gamma = rand(n_panels)
+    gamma_new = similar(gamma)
+    AIC_x = rand(n_panels, n_panels)
+    AIC_y = similar(AIC_x)
+    AIC_z = similar(AIC_x)
+    v_ind = zeros(3)
+    point = rand(3)
+    va_norm_array = ones(n_panels)
+    va_unit_array = ones(n_panels, 3)
+    
+    models = ["VSM", "LLT"]
+    core_radius_fractions = [0.001, 10.0]
+
+    @testset "AIC Matrix Calculation" begin
+        for model in models
+            for frac in core_radius_fractions
+                result = @benchmark calculate_AIC_matrices($wing_aero, $model, $frac, $va_norm_array, $va_unit_array)
+                @test result.allocs ≤ 100  # Allow some allocations for matrix setup
+            end
+        end
+    end
+    
+    @testset "Gamma Loop" begin
+        result = @benchmark gamma_loop($solver, $wing, $gamma_new, $AIC_x, $AIC_y, $AIC_z)
+        @test result.allocs ≤ 50  # Main iteration should be mostly allocation-free
+    end
+    
+    @testset "Results Calculation" begin
+        result = @benchmark calculate_results($wing, $gamma)
+        @test result.allocs ≤ 20  # Allow minimal allocations for results
+    end
+    
+    @testset "Angle of Attack Update" begin
+        result = @benchmark update_effective_angle_of_attack_if_VSM($wing, $gamma)
+        @test result.allocs == 0  # Should be allocation-free
+    end
+    
+    @testset "Area Calculations" begin
+        result = @benchmark calculate_projected_area($wing)
+        @test result.allocs ≤ 10  # Geometric calculations may need some allocations
+    end
+    
+    @testset "Aerodynamic Coefficients" begin
+        panel = panels[1]
+        alpha = 0.1
+        
+        @test (@ballocated calculate_cl($panel, $alpha)) == 0
+        @test (@ballocated calculate_cd_cm($panel, $alpha)) == 0
+    end
+    
+    @testset "Induced Velocity Calculations" begin
+        # Test single ring velocity calculation
+        @test (@ballocated calculate_velocity_induced_single_ring_semiinfinite(
+            $point, $panels[1], $gamma[1])) == 0
+            
+        # Test 2D bound vortex
+        @test (@ballocated calculate_velocity_induced_bound_2D(
+            $point, $panels[1], $gamma[1])) == 0
+            
+        # Test 3D velocity components
+        @test (@ballocated velocity_3D_bound_vortex!(
+            $v_ind, $point, $panels[1], $gamma[1])) == 0
+            
+        @test (@ballocated velocity_3D_trailing_vortex!(
+            $v_ind, $point, $panels[1], $gamma[1])) == 0
+            
+        @test (@ballocated velocity_3D_trailing_vortex_semiinfinite!(
+            $v_ind, $point, $panels[1], $gamma[1])) == 0
+    end
+end