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106 lines
3.5 KiB
Python
106 lines
3.5 KiB
Python
import pytest
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import numpy as np
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from build123d import Airfoil, Vector, Edge, Wire
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# --- parse_naca4 tests ------------------------------------------------------
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@pytest.mark.parametrize(
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"code, expected",
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[
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("2412", (0.02, 0.4, 0.12)), # standard NACA 2412
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("0012", (0.0, 0.0, 0.12)), # symmetric section
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("2213.323", (0.02, 0.2, 0.13323)), # fractional thickness
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("NACA2412", (0.02, 0.4, 0.12)), # with prefix
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],
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)
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def test_parse_naca4_variants(code, expected):
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m, p, t = Airfoil.parse_naca4(code)
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np.testing.assert_allclose([m, p, t], expected, rtol=1e-6)
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# --- basic construction tests -----------------------------------------------
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def test_airfoil_basic_construction():
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airfoil = Airfoil("2412", n_points=40)
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assert isinstance(airfoil, Airfoil)
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assert isinstance(airfoil.camber_line, Edge)
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assert isinstance(airfoil._camber_points, list)
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assert all(isinstance(p, Vector) for p in airfoil._camber_points)
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# Check metadata
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assert airfoil.code == "2412"
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assert pytest.approx(airfoil.max_camber, rel=1e-6) == 0.02
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assert pytest.approx(airfoil.camber_pos, rel=1e-6) == 0.4
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assert pytest.approx(airfoil.thickness, rel=1e-6) == 0.12
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assert airfoil.finite_te is False
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def test_airfoil_finite_te_profile():
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"""Finite trailing edge version should have a line closing the profile."""
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airfoil = Airfoil("2412", finite_te=True, n_points=40)
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assert isinstance(airfoil, Wire)
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assert airfoil.finite_te
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assert len(list(airfoil.edges())) == 2
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def test_airfoil_infinite_te_profile():
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"""Infinite trailing edge (periodic spline)."""
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airfoil = Airfoil("2412", finite_te=False, n_points=40)
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assert isinstance(airfoil, Wire)
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# Should contain a single closed Edge
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assert len(airfoil.edges()) == 1
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assert airfoil.edges()[0].is_closed
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# --- geometric / numerical validity -----------------------------------------
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def test_camber_line_geometry_monotonic():
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"""Camber x coordinates should increase monotonically along the chord."""
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af = Airfoil("2412", n_points=80)
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x_coords = [p.X for p in af._camber_points]
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assert np.all(np.diff(x_coords) >= 0)
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def test_airfoil_chord_limits():
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"""Airfoil should be bounded between x=0 and x=1."""
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af = Airfoil("2412", n_points=100)
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all_points = af._camber_points
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xs = np.array([p.X for p in all_points])
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assert xs.min() >= -1e-9
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assert xs.max() <= 1.0 + 1e-9
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def test_airfoil_thickness_scaling():
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"""Check that airfoil thickness scales linearly with NACA last two digits."""
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af1 = Airfoil("0010", n_points=120)
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af2 = Airfoil("0020", n_points=120)
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# Extract main surface edge (for finite_te=False it's just one edge)
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edge1 = af1.edges()[0]
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edge2 = af2.edges()[0]
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# Sample many points along each edge
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n = 500
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ys1 = [(edge1 @ u).Y for u in np.linspace(0.0, 1.0, n)]
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ys2 = [(edge2 @ u).Y for u in np.linspace(0.0, 1.0, n)]
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# Total height (max - min)
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h1 = max(ys1) - min(ys1)
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h2 = max(ys2) - min(ys2)
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# For symmetric NACA 00xx, thickness is proportional to 't'
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assert (h1 / h2) == pytest.approx(0.5, rel=0.05)
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def test_camber_line_is_centered():
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"""Mean of upper and lower surfaces should approximate camber line."""
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af = Airfoil("2412", n_points=50)
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# Extract central camber Y near mid-chord
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mid_index = len(af._camber_points) // 2
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mid_point = af._camber_points[mid_index]
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# Camber line should be roughly symmetric around y=0 for small m
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assert abs(mid_point.Y) < 0.05
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