def test_conventional():
from aerosandbox.aerodynamics.aero_3D.test_aero_3D.geometries.conventional import airplane
analysis = asb.VortexLatticeMethod(
airplane=airplane,
op_point=asb.OperatingPoint(alpha=10),
)
return analysis.run()
def get_aero(alpha, taper_ratio):
airplane = asb.Airplane(wings=[
asb.Wing(symmetric=True,
xsecs=[
asb.WingXSec(
xyz_le=[-0.25, 0, 0],
chord=1,
),
asb.WingXSec(
xyz_le=[-0.25 * taper_ratio, 1, 0],
chord=taper_ratio,
)
])
])
op_point = asb.OperatingPoint(
velocity=1,
alpha=alpha,
)
vlm = asb.VortexLatticeMethod(
airplane,
op_point,
chordwise_resolution=6,
spanwise_resolution=6,
)
return vlm.run()
def test_flat_plate_mirrored():
from aerosandbox.aerodynamics.aero_3D.test_aero_3D.geometries.flat_plate_mirrored import airplane
analysis = asb.VortexLatticeMethod(
airplane=airplane,
op_point=asb.OperatingPoint(alpha=10),
spanwise_resolution=1,
chordwise_resolution=3,
)
return analysis.run()
def LD_from_alpha(alpha):
op_point = asb.OperatingPoint(
velocity=1,
alpha=alpha,
)
vlm = asb.VortexLatticeMethod(airplane,
op_point,
align_trailing_vortices_with_wind=True)
aero = vlm.run()
CD0 = 0.01
LD = aero["CL"] / (aero["CD"] + CD0)
return LD
import aerosandbox.numpy as np
for i, wing in enumerate(airplane.wings):
for j, xsec in enumerate(wing.xsecs):
af = xsec.airfoil
af.generate_polars(
cache_filename=f"cache/{af.name}.json",
xfoil_kwargs=dict(xfoil_repanel="naca" in af.name.lower()))
airplane.wings[i].xsecs[j].airfoil = af
op_point = asb.OperatingPoint(velocity=25, alpha=3)
vlm = asb.VortexLatticeMethod(
airplane,
op_point,
align_trailing_vortices_with_wind=True,
chordwise_resolution=12,
spanwise_resolution=12,
)
vlm_aero = vlm.run()
ab = asb.AeroBuildup(airplane, op_point)
ab_aero = ab.run()
avl = asb.AVL(
airplane,
op_point,
)
avl_aero = avl.run()
for k, v in {"VLM": vlm_aero, "AVL": avl_aero, "AB": ab_aero}.items():
analysis = asb.VortexLatticeMethod(
airplane=airplane,
op_point=asb.OperatingPoint(alpha=10),
)
return analysis.run()
def test_flat_plate_mirrored():
from aerosandbox.aerodynamics.aero_3D.test_aero_3D.geometries.flat_plate_mirrored import airplane
analysis = asb.VortexLatticeMethod(
airplane=airplane,
op_point=asb.OperatingPoint(alpha=10),
spanwise_resolution=1,
chordwise_resolution=3,
)
return analysis.run()
if __name__ == '__main__':
# test_conventional()
# test_vanilla()
# test_flat_plate()['CL']
# test_flat_plate_mirrored()
# pytest.main()
from aerosandbox.aerodynamics.aero_3D.test_aero_3D.geometries.conventional import airplane
analysis = asb.VortexLatticeMethod(
airplane=airplane,
op_point=asb.OperatingPoint(alpha=10),
)
aero = analysis.run()
analysis.draw()