def cfd_table():
af = MyTools.airfoil.airfoil.Airfoil()
af.read_txt('Clark-Y.txt')
af.display()
#Mach = np.arange(0.2, 0.9, 0.05)
Mach = np.array([0.90])
aseq = np.arange(-20., 21., 2.0)
pth = 'ClarkY-C81.txt'
fc = FlightConditions(0.2,0.0)
scale = 1.0
yplus = 1.0
# fid = open(pth,'wt')
# fid.write('Mach\talpha\tCL\tCD\tCM\n')
# fid.close()
#
idx = 14
for M in Mach:
fc.set_speed(M)
idx += 1
for a in aseq:
fid = open(pth,'at')
cl,cd,cm,gs = cfd.run_analysis(af,fc,a,yplus,scale, idx)
fid.write('%.4f\t%.4f\t%.8f\t%.8f\t%.8f\n'%(M,a,cl,cd,cm))
fid.close()
class CFDrun:
def __init__(self, af,path=None):
self.fc = FlightConditions(0.2, 0.0)
self.scale = 1.0
self.af = af
self.yplus = 1.0
self.xl = np.array([0.2, -20.0]) #Mach, alpha
self.xu = np.array([0.8, 20.0])
self.norm = mt.Normalization(self.xl, self.xu,-1.0,1.0)
self.idx = 0
if path==None:
self.path = 'ClarkY-hifiCFD.txt'
else:
self.path = path
fid = open(self.path,'wt')
fid.write('Mach\talpha\tcl\tcd\tcm\n')
fid.close()
def __call__(self,x):
self.idx += 1
x = self.norm.denormalize(x)
Mach = x[0]
alpha = x[1]
self.fc.set_speed(Mach)
cl,cd,cm,gs = cfd.run_analysis(self.af,self.fc,alpha,self.yplus,self.scale, self.idx)
self.save(Mach,alpha,cl,cd,cm)
return cl, cd, cm
def save(self,M,a,cl,cd,cm):
fid = open(self.path,'at')
fid.write('%.8f\t%.8f\t%.8f\t%.8f\t%.8f\n'%(M,a,cl,cd,cm))
fid.close()
def main():
af = MyTools.airfoil.airfoil.Airfoil()
af.create_naca4()
Mach = np.arange(0.2, 0.9, 0.1)
aseq = [-20, 20, 4.0]
fc = FlightConditions(0.2,0.0)
fid = open('aero_data_jfoil.txt','wt')
for M in Mach:
fc.set_speed(M)
pol = af.get_jfoil_polar(M,fc.Re,aseq)
for a,cl,cd,cm in zip(pol.alpha, pol.cl, pol.cd, pol.cm):
fid.write('%.2f\t%.2f\t%.6f\t%.6f\t%.6f\n'%(M,a,cl,cd,cm))
fid.close()