def main(x1, x2, y1, y2, y3, aoas=(7.42), target_dir=""):
""" create a LaWGS file for twisted rectangular wing
reference case 3"""
wgs = wgs_creator.LaWGS("ADODG_case3")
n_wing_x = 30
n_wing_y = 30
n_wing_z = 8
chord_wing = 1.
halfspan_wing = chord_wing * 3
# define twist distribution
cv = np.array(((0, 0),
(x1, y1),
(x2, y2),
(1, y3)))
twist_func = bspline(cv, degree=3, periodic=False)
twist_xy = twist_func(np.linspace(0, 1, 150))
twist_dist = interp1d(twist_xy[:,0] * halfspan_wing, twist_xy[:,1])
# create wing
base_airfoil = wgs_creator.naca4digit("0010", num=n_wing_x, chord=chord_wing)
wing = list()
span_pos = np.linspace(0, halfspan_wing, n_wing_y)
for y in span_pos:
rot_foil = base_airfoil.roty(base_airfoil[0], twist_dist(y))
rot_foil.shift((0, y, 0), inplace=True)
wing.append(rot_foil)
wing = wgs_creator.Network(wing)
wgs.append_network("wing", wing, 1)
# create wingtip
degs = np.linspace(0, -180, n_wing_z)
wingtipu, _ = base_airfoil.shift((0, halfspan_wing, 0)).split_half()
wingtip = [wingtipu.rotx(wingtipu[0], d) for d in degs]
wingtip = wgs_creator.Network(wingtip)
wingtip = wingtip.roty(wingtipu[0], twist_dist(halfspan_wing))
wgs.append_network("wingtip", wingtip, 1)
# add wake
wake_length = chord_wing * 50.
wingwake = wing.make_wake(3, wake_length)
wgs.append_network("wingwake", wingwake, 18)
wgs.create_wgs(os.path.join(target_dir, "ADODG_case3.wgs"))
span = halfspan_wing * 2
sref = chord_wing * span
xref = chord_wing * 0.25
aux_name = os.path.join(target_dir, "ADODG_case3.aux")
wgs.create_aux(filename=aux_name, alpha=aoas, mach=0.5, cbar=chord_wing, span=span, sref=sref,
xref=xref, zref=0.)
def main(twist_func, aoas=(7.42), target_dir=""):
""" create a LaWGS file for twisted rectangular wing
reference case 3"""
wgs = wgs_creator.LaWGS("ADODG_case3")
n_wing_x = 40
n_wing_y = 40
n_wing_z = 12
chord_wing = 100.
halfspan_wing = chord_wing * 3
# define twist distribution
twist_xy = twist_func(np.linspace(0, 1, 150))
twist_dist = interp1d(twist_xy[:, 0] * halfspan_wing, twist_xy[:, 1])
# create wing
base_airfoil = wgs_creator.naca4digit("0010",
num=n_wing_x,
chord=chord_wing)
wing = list()
span_pos = np.linspace(0, halfspan_wing, n_wing_y)
for y in span_pos:
twist = twist_dist(y)
rot_foil = base_airfoil.roty(base_airfoil[0], twist)
local_chord = np.max(rot_foil[:, 0]) - np.min(rot_foil[:, 0])
rot_foil *= chord_wing / local_chord
rot_foil.shift((0, y, 0), inplace=True)
wing.append(rot_foil)
wing = wgs_creator.Network(wing)
wgs.append_network("wing", wing, 1)
# create wingtip
degs = np.linspace(0, -180, n_wing_z)
wingtipu, _ = base_airfoil.shift((0, 0, 0)).split_half()
wingtip = [wingtipu.rotx(wingtipu[0], d) for d in degs]
wingtip = wgs_creator.Network(wingtip)
twist = twist_dist(y)
wingtip = wingtip.roty(wingtipu[0], twist_dist(halfspan_wing))
local_chord = np.max(wingtip[0, :, 0]) - np.min(wingtip[0, :, 0])
wingtip *= chord_wing / local_chord
wingtip.shift((0, halfspan_wing, 0), inplace=True)
wgs.append_network("wingtip", wingtip, 1)
# add wake
wake_length = chord_wing * 50.
wingwake = wing.make_wake(3, wake_length)
wgs.append_network("wingwake", wingwake, 18)
wgs.create_wgs(os.path.join(target_dir, "ADODG_case3.wgs"))
span = halfspan_wing * 2
sref = chord_wing * span / 100 # multiply aerodynamic coefficients by 100
xref = chord_wing * 0.25
aux_name = os.path.join(target_dir, "ADODG_case3.aux")
wgs.create_aux(filename=aux_name,
alpha=aoas,
mach=0.5,
cbar=chord_wing,
span=span,
sref=sref,
xref=xref,
zref=0.)
'''
for full documentation, see tutorial 3
'''
import numpy as np
from pyPanair.preprocess import wgs_creator
# Init
wgs = wgs_creator.LaWGS("main")
# Airfoil
root_airfoil = wgs_creator.read_airfoil("AGARDB/mwe.csv",
y_coordinate=0.5,
expansion_ratio=2.598)
root_airfoil = root_airfoil.shift((4.5, 0., 0.))
tip_airfoil = root_airfoil.replace(x=7.098, y=2., z=0.)
wing = root_airfoil.linspace(tip_airfoil, num=20)
wgs.append_network("wing", wing, 1)
# Nose + Forebody
n_nose = 5 # number of points in the line
x_nose = np.linspace(0., 3., num=n_nose) # x-coordinates of the line
y_nose = x_nose / 3 * (1 - 1 / 9 * (x_nose)**2 + 1 / 54 *
(x_nose)**3) # y-coordinates of the line
nose_line = wgs_creator.Line(np.zeros((n_nose, 3))) # create an array of zeros
nose_line[:, 0] = x_nose
nose_line[:, 1] = y_nose
fbody_p1 = wgs_creator.Point(
nose_line[-1]) # point at the end of the nose_line
fbody_p2 = fbody_p1.replace(x=4.5)