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Rename to more logical name
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‎test/solver/test_unrefined_dist.jl‎

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using VortexStepMethod
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using LinearAlgebra
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using Test
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@testset "Unrefined Arrays Tests" begin
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@testset "Unrefined section array aggregation" begin
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# Create a simple wing with unrefined sections
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n_panels = 20
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n_unrefined_sections = 5 # 5 unrefined sections
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# Create a test wing settings file
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settings_file = create_temp_wing_settings("solver", "solver_test_wing.yaml"; alpha=5.0, beta=0.0, wind_speed=10.0)
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try
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# Modify settings to use specific panel configuration
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settings = VSMSettings(settings_file)
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settings.wings[1].n_panels = n_panels
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settings.solver_settings.n_panels = n_panels
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# Create wing and solver
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wing = Wing(settings)
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body_aero = BodyAerodynamics([wing])
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solver = Solver(body_aero, settings)
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# Set conditions and solve
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va = [10.0, 0.0, 0.0]
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set_va!(body_aero, va)
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sol = solve!(solver, body_aero)
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# Test 1: Unrefined arrays exist and have correct size
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@test length(sol.cl_unrefined_dist) == wing.n_unrefined_sections
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@test length(sol.cd_unrefined_dist) == wing.n_unrefined_sections
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@test length(sol.cm_unrefined_dist) == wing.n_unrefined_sections
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# Test 2: Unrefined arrays are not all zeros (solver computed them)
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@test !all(sol.cl_unrefined_dist .== 0.0)
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@test !all(sol.cd_unrefined_dist .== 0.0)
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# Test 3: Verify unrefined coefficients are averaged from refined panels
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# refined_panel_mapping maps each refined panel to its unrefined section index
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for unrefined_idx in 1:wing.n_unrefined_sections
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# Find all refined panels that map to this unrefined section
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refined_panel_indices = findall(x -> x == unrefined_idx, wing.refined_panel_mapping)
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if !isempty(refined_panel_indices)
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# Calculate expected average from refined panel coefficients
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expected_cl = sum(sol.cl_dist[refined_panel_indices]) / length(refined_panel_indices)
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expected_cd = sum(sol.cd_dist[refined_panel_indices]) / length(refined_panel_indices)
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expected_cm = sum(sol.cm_dist[refined_panel_indices]) / length(refined_panel_indices)
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# Check if unrefined coefficients match expected averages
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# Handle NaN values that can occur in INVISCID models
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if isnan(expected_cl)
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@test isnan(sol.cl_unrefined_dist[unrefined_idx])
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else
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@test isapprox(sol.cl_unrefined_dist[unrefined_idx], expected_cl, rtol=1e-10)
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end
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if isnan(expected_cd)
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@test isnan(sol.cd_unrefined_dist[unrefined_idx])
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else
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@test isapprox(sol.cd_unrefined_dist[unrefined_idx], expected_cd, rtol=1e-10)
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end
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if isnan(expected_cm)
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@test isnan(sol.cm_unrefined_dist[unrefined_idx])
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else
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@test isapprox(sol.cm_unrefined_dist[unrefined_idx], expected_cm, rtol=1e-10)
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end
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end
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end
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# Test 4: Verify physical consistency (lift coefficients should be positive at positive AoA)
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# Skip test if values are NaN
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if !any(isnan.(sol.cl_unrefined_dist))
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@test all(sol.cl_unrefined_dist .> 0.0)
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end
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finally
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rm(settings_file; force=true)
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end
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end
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@testset "Unrefined arrays with different panel counts" begin
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# Test with various panel/section combinations
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test_cases = [
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(n_panels=40, n_unrefined_expected=21), # From YAML file sections
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(n_panels=30, n_unrefined_expected=21),
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(n_panels=24, n_unrefined_expected=21),
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]
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for (n_panels, n_unrefined_expected) in test_cases
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settings_file = create_temp_wing_settings("solver", "solver_test_wing.yaml"; alpha=5.0, beta=0.0, wind_speed=10.0)
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try
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settings = VSMSettings(settings_file)
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settings.wings[1].n_panels = n_panels
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settings.solver_settings.n_panels = n_panels
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wing = Wing(settings)
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body_aero = BodyAerodynamics([wing])
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solver = Solver(body_aero, settings)
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va = [10.0, 0.0, 0.0]
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set_va!(body_aero, va)
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sol = solve!(solver, body_aero)
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# Verify arrays have correct size
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@test length(sol.cl_unrefined_dist) == wing.n_unrefined_sections
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@test length(sol.cd_unrefined_dist) == wing.n_unrefined_sections
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@test length(sol.cm_unrefined_dist) == wing.n_unrefined_sections
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# Verify unrefined coefficients are computed correctly using mapping
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for unrefined_idx in 1:wing.n_unrefined_sections
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refined_panel_indices = findall(x -> x == unrefined_idx, wing.refined_panel_mapping)
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if !isempty(refined_panel_indices)
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expected_cl = sum(sol.cl_dist[refined_panel_indices]) / length(refined_panel_indices)
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expected_cd = sum(sol.cd_dist[refined_panel_indices]) / length(refined_panel_indices)
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expected_cm = sum(sol.cm_dist[refined_panel_indices]) / length(refined_panel_indices)
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# Handle NaN for all coefficients
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if isnan(expected_cl)
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@test isnan(sol.cl_unrefined_dist[unrefined_idx])
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else
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@test isapprox(sol.cl_unrefined_dist[unrefined_idx], expected_cl, rtol=1e-10)
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end
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if isnan(expected_cd)
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@test isnan(sol.cd_unrefined_dist[unrefined_idx])
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else
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@test isapprox(sol.cd_unrefined_dist[unrefined_idx], expected_cd, rtol=1e-10)
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end
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if isnan(expected_cm)
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@test isnan(sol.cm_unrefined_dist[unrefined_idx])
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else
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@test isapprox(sol.cm_unrefined_dist[unrefined_idx], expected_cm, rtol=1e-10)
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end
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end
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end
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finally
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rm(settings_file; force=true)
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end
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end
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end
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end

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