def vandevooren(cls, tau=0.05, epsilon=0.05, numpoints=100):
from paraBEM.airfoil.conformal_mapping import VanDeVoorenAirfoil
airfoil = VanDeVoorenAirfoil(tau=tau, epsilon=epsilon)
profile = [[c.real, c.imag] for c in airfoil.coordinates(numpoints)]
# find the smallest xvalue to reset the nose
x = numpy.array([i[0] for i in profile])
profile = cls(profile, "VanDeVooren_tau=" + str(tau) + "_epsilon=" + str(epsilon))
profile.normalize(numpy.where(x == min(x))[0][0])
profile.normalize()
profile.numpoints = numpoints
return profile
def vandevooren(cls, tau=0.05, epsilon=0.05, numpoints=100):
from paraBEM.airfoil.conformal_mapping import VanDeVoorenAirfoil
airfoil = VanDeVoorenAirfoil(tau=tau, epsilon=epsilon)
profile = [[c.real, c.imag] for c in airfoil.coordinates(numpoints)]
# find the smallest xvalue to reset the nose
x = numpy.array([i[0] for i in profile])
profile = cls(
profile,
"VanDeVooren_tau=" + str(tau) + "_epsilon=" + str(epsilon))
profile.normalize(numpy.where(x == min(x))[0][0])
profile.normalize()
profile.numpoints = numpoints
return profile
from paraBEM.vtk_export import VtkWriter
from paraBEM.utils import check_path
####################################################
# analytic solution of vandevooren-airfoils #
####################################################
# -inputparameter for the vandevooren airfoil
alpha = np.deg2rad(10) # alpha is the angle of attack in rad
tau = np.deg2rad(1) # tau is the angle of the trailing edge
epsilon = 0.10 # epsilon is the thickness-parameter
num_x = 300 # number of plot-points in x-direction
num_y = 300 # number of plot-points in y-direction
# -create joukowsky object
airfoil = VanDeVoorenAirfoil(tau=tau, epsilon=epsilon)
# -helper functions
def complex_to_3vec(z):
return [z.real, z.imag, 0]
def zeta_velocity(z):
vel = airfoil.velocity(z, alpha)
return [vel.real, -vel.imag, 0.]
def z_velocity(z):
vel = airfoil.z_velocity(z, alpha)
from paraBEM.vtk_export import VtkWriter
from paraBEM.utils import check_path
####################################################
# analytic solution of vandevooren-airfoils #
####################################################
# -inputparameter for the vandevooren airfoil
alpha = np.deg2rad(10) # alpha is the angle of attack in rad
tau = np.deg2rad(1) # tau is the angle of the trailing edge
epsilon = 0.10 # epsilon is the thickness-parameter
num_x = 300 # number of plot-points in x-direction
num_y = 300 # number of plot-points in y-direction
# -create joukowsky object
airfoil = VanDeVoorenAirfoil(tau=tau, epsilon=epsilon)
# -helper functions
def complex_to_3vec(z):
return [z.real, z.imag, 0]
def zeta_velocity(z):
vel = airfoil.velocity(z, alpha)
return [vel.real, -vel.imag, 0.]
def z_velocity(z):
vel = airfoil.z_velocity(z, alpha)