|
| 1 | +using VortexStepMethod |
| 2 | +using LinearAlgebra |
| 3 | +using Test |
| 4 | + |
| 5 | +""" |
| 6 | + scaled_wing_aero(scale) |
| 7 | +
|
| 8 | +A rectangular wing with a constant nonzero `cm`, every length multiplied by `scale`, |
| 9 | +at an inflow that does not depend on it. |
| 10 | +""" |
| 11 | +function scaled_wing_aero(scale) |
| 12 | + chord, span = 1.5scale, 6.0scale |
| 13 | + alpha_range = deg2rad.([-10.0, 0.0, 10.0]) |
| 14 | + polar = (alpha_range, [-0.6, 0.4, 1.4], fill(0.02, 3), fill(-0.08, 3)) |
| 15 | + wing = Wing(10) |
| 16 | + add_section!(wing, [0.0, span / 2, 0.0], [chord, span / 2, 0.0], POLAR_VECTORS, polar) |
| 17 | + add_section!(wing, [0.0, -span / 2, 0.0], [chord, -span / 2, 0.0], POLAR_VECTORS, |
| 18 | + polar) |
| 19 | + refine!(wing) |
| 20 | + body_aero = BodyAerodynamics([wing]) |
| 21 | + set_va!(body_aero, [20.0, 0.0, 2.0]) |
| 22 | + return body_aero |
| 23 | +end |
| 24 | + |
| 25 | +@testset "moments carry N·m: lengths scaled by k scale them by k³" begin |
| 26 | + # at fixed inflow and coefficients, N scales as k², N·m as k³, and N·m per |
| 27 | + # unit span as k²; a moment short of one chord factor scales as k² instead |
| 28 | + k = 2.0 |
| 29 | + reference_point(scale) = scale .* [-0.4, 0.3, 0.2] |
| 30 | + |
| 31 | + @testset "solve!" begin |
| 32 | + small, large = map((1.0, k)) do scale |
| 33 | + body_aero = scaled_wing_aero(scale) |
| 34 | + solve!(Solver(body_aero; reference_point=reference_point(scale)), body_aero) |
| 35 | + end |
| 36 | + @test small.solver_status == large.solver_status == FEASIBLE |
| 37 | + @test all(!iszero, small.panel_moment_dist) |
| 38 | + @test large.force ≈ k^2 .* small.force rtol = 1e-6 |
| 39 | + @test large.moment ≈ k^3 .* small.moment rtol = 1e-6 |
| 40 | + @test large.m_body_3D ≈ k^3 .* small.m_body_3D rtol = 1e-6 |
| 41 | + @test large.moment_dist ≈ k^3 .* small.moment_dist rtol = 1e-6 |
| 42 | + @test large.moment_unrefined_dist ≈ k^3 .* small.moment_unrefined_dist rtol = 1e-6 |
| 43 | + @test large.panel_moment_dist ≈ k^2 .* small.panel_moment_dist rtol = 1e-6 |
| 44 | + @test large.moment_coeffs ≈ small.moment_coeffs rtol = 1e-6 |
| 45 | + @test large.moment_coeff_dist ≈ small.moment_coeff_dist rtol = 1e-6 |
| 46 | + end |
| 47 | + |
| 48 | + @testset "solve" begin |
| 49 | + small, large = map((1.0, k)) do scale |
| 50 | + body_aero = scaled_wing_aero(scale) |
| 51 | + solve(Solver(body_aero), body_aero; reference_point=reference_point(scale)) |
| 52 | + end |
| 53 | + for key in ("Mx", "My", "Mz", "M_distribution") |
| 54 | + @test large[key] ≈ k^3 .* small[key] rtol = 1e-6 |
| 55 | + end |
| 56 | + for key in ("cmx", "cmy", "cmz") |
| 57 | + @test large[key] ≈ small[key] rtol = 1e-6 |
| 58 | + end |
| 59 | + end |
| 60 | +end |
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