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Restore test
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‎test/solver/test_solver.jl‎

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@@ -29,195 +29,4 @@ using Test
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rm(settings_file; force=true)
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end
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end
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@testset "Solver with n_groups=0" begin
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# Test that solver works correctly when n_groups=0 (no group functionality)
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settings_file = create_temp_wing_settings("solver", "solver_test_wing.yaml";
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alpha=5.0, beta=0.0, wind_speed=10.0, n_groups=0)
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try
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settings = VSMSettings(settings_file)
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wing = Wing(settings)
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@test wing.n_groups == 0
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body_aero = BodyAerodynamics([wing])
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solver = Solver(body_aero, settings)
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# Verify solver has zero groups
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@test length(solver.sol.group_moment_dist) == 0
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@test length(solver.sol.group_moment_coeff_dist) == 0
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# Test that solve! works without errors
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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 sol isa VSMSolution
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@test sol.solver_status == FEASIBLE
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# Verify that group moments are empty
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@test length(sol.group_moment_dist) == 0
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@test length(sol.group_moment_coeff_dist) == 0
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# But force and moment should still be computed
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@test !all(sol.force .== 0.0)
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@test norm(sol.force) > 0
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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 "Linearize with n_groups=0" begin
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# Test that linearize works correctly when n_groups=0
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settings_file = create_temp_wing_settings("solver", "solver_test_wing.yaml";
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alpha=5.0, beta=0.0, wind_speed=10.0, n_groups=0, n_panels=4)
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try
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settings = VSMSettings(settings_file)
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wing = Wing(settings)
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@test wing.n_groups == 0
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body_aero = BodyAerodynamics([wing])
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solver = Solver(body_aero, settings)
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# Set velocity
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va = [10.0, 0.0, 0.0]
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set_va!(body_aero, va)
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# Test linearize with only velocity (no theta or delta since n_groups=0)
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y = va # Only velocity in input vector
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jac, results = VortexStepMethod.linearize(
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solver,
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body_aero,
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y;
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theta_idxs=nothing,
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delta_idxs=nothing,
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va_idxs=1:3,
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omega_idxs=nothing
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)
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# Results should only have 6 elements (force + moment, no group moments)
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@test length(results) == 6
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@test size(jac) == (6, 3) # 6 outputs, 3 inputs (vx, vy, vz)
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# Verify forces are non-zero
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@test norm(results[1:3]) > 0
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# Test that using theta_idxs with n_groups=0 throws an error
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@test_throws ArgumentError VortexStepMethod.linearize(
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solver,
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body_aero,
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[0.0, 10.0, 0.0, 0.0]; # Invalid: trying to use theta
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theta_idxs=1:1,
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va_idxs=2:4
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)
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# Test that using delta_idxs with n_groups=0 throws an error
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@test_throws ArgumentError VortexStepMethod.linearize(
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solver,
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body_aero,
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[0.0, 10.0, 0.0, 0.0]; # Invalid: trying to use delta
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delta_idxs=1:1,
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va_idxs=2:4
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)
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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 "Linearize theta_idxs validation" begin
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# Test that theta_idxs length must match n_groups
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settings_file = create_temp_wing_settings("solver", "solver_test_wing.yaml";
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alpha=5.0, beta=0.0, wind_speed=10.0, n_groups=2, n_panels=4)
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try
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settings = VSMSettings(settings_file)
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wing = Wing(settings)
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@test wing.n_groups == 2
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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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# Test with correct number of theta angles (2)
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y_correct = [0.0, 0.0, 10.0, 0.0, 0.0] # 2 theta + 3 va
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jac, results = VortexStepMethod.linearize(
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solver,
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body_aero,
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y_correct;
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theta_idxs=1:2,
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va_idxs=3:5
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)
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@test size(jac, 1) == 8 # 6 + 2 group moments
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# Test with wrong number of theta angles (should throw error)
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y_wrong = [0.0, 0.0, 0.0, 0.0, 10.0, 0.0, 0.0] # 4 theta + 3 va
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@test_throws ArgumentError VortexStepMethod.linearize(
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solver,
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body_aero,
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y_wrong;
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theta_idxs=1:4, # Wrong: 4 angles but only 2 groups
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va_idxs=5:7
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)
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# Test with wrong number of delta angles
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@test_throws ArgumentError VortexStepMethod.linearize(
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solver,
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body_aero,
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y_wrong;
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delta_idxs=1:4, # Wrong: 4 angles but only 2 groups
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va_idxs=5:7
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)
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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 "Wing type cannot deform" begin
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# Test that regular Wing type (YAML-based) cannot use group_deform!
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settings_file = create_temp_wing_settings("solver", "solver_test_wing.yaml";
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alpha=5.0, beta=0.0, wind_speed=10.0, n_groups=2, n_panels=4)
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try
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settings = VSMSettings(settings_file)
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wing = Wing(settings)
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@test wing isa Wing
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@test wing.n_groups == 2
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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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# Test that trying to use theta angles with Wing throws an error
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y = [0.0, 0.0, 10.0, 0.0, 0.0] # 2 theta + 3 va
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@test_throws ArgumentError VortexStepMethod.linearize(
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solver,
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body_aero,
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y;
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theta_idxs=1:2,
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va_idxs=3:5
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)
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# But linearize should work fine with only velocity (no deformation)
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y_velocity_only = [10.0, 0.0, 0.0]
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jac, results = VortexStepMethod.linearize(
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solver,
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body_aero,
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y_velocity_only;
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theta_idxs=nothing,
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va_idxs=1:3
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)
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@test size(jac, 1) == 8 # 6 + 2 group moments
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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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