Add bench_solve.jl

Author: ufechner7

test/bench_solve.jl

@@ -0,0 +1,57 @@
+# DO NOT DELETE, DO NOT MODIFY!
+# This script will not be included in run_tests.jl
+# It shall only be executed on one and the same machine for benchmarking the solve functions
+using LinearAlgebra
+using VortexStepMethod
+using BenchmarkTools
+using Test
+
+using Pkg
+
+if !("CSV" ∈ keys(Pkg.project().dependencies))
+    using TestEnv
+    TestEnv.activate()
+end
+
+# Step 1: 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)
+
+# Step 2: Create wing geometry with linear panel distribution
+wing = Wing(n_panels, spanwise_distribution=LINEAR)
+
+# Add wing sections - defining only tip sections with inviscid airfoil model
+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)
+
+# Step 3: Initialize aerodynamics
+wa = BodyAerodynamics([wing])
+
+# Set inflow conditions
+vel_app = [cos(alpha), 0.0, sin(alpha)] .* v_a
+set_va!(wa, vel_app)
+
+# Step 4: Initialize solvers for both LLT and VSM methods
+vsm_solver = Solver(wa; aerodynamic_model_type=VSM)
+
+# Step 5: Solve using both methods
+result = @benchmark  solve_base!($vsm_solver, $wa, nothing)  # 34 allocations
+println("solve_base():")
+println("Allocations: ", result.allocs, ", Mean time: ", round(mean(result.times)/1000), " µs")
+# time Python: 32.0 ms  Ryzen 7950x
+# time Julia:   0.45 ms Ryzen 7950x
+result = @benchmark  sol = solve!($vsm_solver, $wa, nothing) # 68 allocations
+println("solve!()")
+println("Allocations: ", result.allocs, ", Mean time: ", round(mean(result.times)/1000), " µs")
+nothing