def rotated_flap(self):
deflected_flap = RotatedShape(
self.wing_parts[1],
self.hinge_points[0], # Rotate around hinge
p2v(self.hinge_points[0]) - p2v(self.hinge_points[1]),
angle=-self.flap_deflection * np.pi / 180)
center_point = v2p(
p2v(self.hinge_points[0]) / 2 +
p2v(self.hinge_points[1]) / 2) # Rotation point for corrections
deflected_flap = RotatedShape(
deflected_flap,
center_point,
Vector(0, 0, 1),
angle=self.z_rot_correction) # Adjust rotation around z axis
return RotatedShape(
deflected_flap,
center_point,
Vector(1, 0, 0),
angle=self.x_rot_correction) # Adjust rotation around x axis
def camber_line(self):
xb, zb, xt, zt = split_coordinates(self.airfoil_coordinates)
x_locations = np.linspace(self.flap_hinge_location, 1, 25)
points_list_1, points_list_2 = [], []
for i in range(len(x_locations)):
z_bottom = interp_coords(xb, zb, x_locations[i])
z_top = interp_coords(xt, zt, x_locations[i])
margin = (x_locations[i] - self.flap_hinge_location) * 0.01
points_list_1.append(
Point(x_locations[i], 0, (z_top + z_bottom) / 2))
points_list_2.append(
Point(x_locations[i], 0, (z_top + z_bottom) / 2 + margin))
lines_1, lines_2 = [], []
for i in range(2):
lines_1.append(
FittedCurve(
np.array(points_list_1) * self.chords[i] +
p2v(self.points[i])))
lines_2.append(
FittedCurve(
np.array(points_list_2) * self.chords[i] +
p2v(self.points[i])))
return lines_1, lines_2
def airfoils(self):
out = [0, 0]
for i in range(2):
scaled_airfoil = ScaledCurve(self.unit_airfoil, factor=self.chords[i], reference_point=Point(0, 0, 0))
out[i] = TranslatedCurve(scaled_airfoil, p2v(self.points[i]))
return out
def flap(self):
return RotatedShape(self.wing_parts.solids[0],
self.hinge_location[0],
vector=p2v(self.hinge_location[1]) -
p2v(self.hinge_location[0]),
angle=self.flap_deflection * np.pi / 180)
def circle_center(self):
out = [0, 0]
for i in range(2):
out[i] = self.point + p2v(self.points[i])
return out
def flap(self):
return RotatedShape(self.wing_parts.solids[0],
self.hinge_points[0],
p2v(self.hinge_points[0]) -
p2v(self.hinge_points[1]),
angle=-self.flap_deflection * np.pi / 180)