def test_get_profile_drag(self):
dp = QuadraticDragPolar(9 * 10**-5 * 1 / (units.degree**2),
0.0001 * 1 / units.degree,
0.01 * units.dimensionless)
self.assertAlmostEqual(dp.get_profile_drag(2 * units.degree), 0.0108,
3)
self.assertAlmostEqual(dp.get_profile_drag(6 * units.degree), 0.0140,
3)
def test_constructor(self):
wing = SimpleTaperedWing(span=3 * units.meter,
root_chord=3 * units.meter,
tip_chord=3 * units.meter,
infinite_wing_lift_slope=1 / units.degree,
aoa_zero_lift=0 * units.degree,
drag_polar=QuadraticDragPolar(
aoa_list, c_d_list),
ac_to_cg=5 * units.inch)
def test_aspect_ratio(self):
wing = SimpleTaperedWing(span=1 * units.meter,
root_chord=0.3 * units.meter,
tip_chord=0.3 * units.meter,
infinite_wing_lift_slope=0.106 / units.degree,
aoa_zero_lift=-1.5 * units.degree,
drag_polar=QuadraticDragPolar(
aoa_list=aoa_list, c_d_list=c_d_list),
ac_to_cg=5 * units.inch,
e=0.95)
expected = 1 * 1 / (1 * 0.3) * units.dimensionless
self.assertEqual(wing.aspect_ratio(), expected)
def test_get_drag(self):
wing = SimpleTaperedWing(span=10 * units.meter,
root_chord=1 * units.meter,
tip_chord=1 * units.meter,
infinite_wing_lift_slope=0.106 / units.degree,
aoa_zero_lift=-1.5 * units.degree,
drag_polar=QuadraticDragPolar(
aoa_list=aoa_list, c_d_list=c_d_list),
ac_to_cg=5 * units.inch,
e=0.95)
self.assertAlmostEqual(wing.get_drag_coefficient(4 * units.degree),
0.0138, 3)
def test_lift_slope(self):
wing = SimpleTaperedWing(span=10 * units.meter,
root_chord=1 * units.meter,
tip_chord=1 * units.meter,
infinite_wing_lift_slope=0.106 / units.degree,
aoa_zero_lift=-1.5 * units.degree,
drag_polar=QuadraticDragPolar(
aoa_list=aoa_list, c_d_list=c_d_list),
ac_to_cg=5 * units.inch,
e=0.95)
self.assertAlmostEqual(
wing.get_wing_lift_slope().to('1/degree').magnitude,
0.088,
places=2)
def test_wing_area(self):
wing = SimpleTaperedWing(span=1 * units.meter,
root_chord=0.3 * units.meter,
tip_chord=0.3 * units.meter,
infinite_wing_lift_slope=0.106 / units.degree,
aoa_zero_lift=-1.5 * units.degree,
drag_polar=QuadraticDragPolar(
aoa_list=aoa_list, c_d_list=c_d_list),
ac_to_cg=5 * units.inch,
e=0.95)
expected = 0.3 * units.meter * units.meter
self.assertEqual(wing.get_wing_area(), expected)
wing = SimpleTaperedWing(span=1 * units.meter,
root_chord=0.4 * units.meter,
tip_chord=0.2 * units.meter,
infinite_wing_lift_slope=0.106 / units.degree,
aoa_zero_lift=-1.5 * units.degree,
drag_polar=QuadraticDragPolar(
aoa_list=aoa_list, c_d_list=c_d_list),
ac_to_cg=5 * units.inch,
e=0.95)
expected = (0.4 + 0.2) / 2 * units.meter * units.meter
self.assertEqual(wing.get_wing_area(), expected)