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()
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 run_cfd(self,x,Mach,alpha,lowFidelity=True):
x = self._get_x(x)
x = self.xNormalization.denormalize(x)
x = x[2:]
self.af = MyTools.airfoil.airfoil.cst_x(x,101)
self.af.set_trailing_edge(self.zTE)
self.fc.set_speed(Mach)
if lowFidelity:
self.runCountLow += 1
scale = self.gridScaleLow
else:
self.runCountHigh += 1
scale = self.gridScaleHigh
self.runCountTotal += 1
tc = self.af.thickness
cl,cd,cm,gs = cfd.run_analysis(self.af,self.fc,alpha,self.yplus,scale,
self.runCountTotal)
self.write_data_cfd(Mach,alpha,x,cl,cd,cm,tc,lowFidelity)
return cl, cd, cm
def main():
Mach = 0.85
alpha = 0.0
variance = 0.025
MachLow = Mach*(1.0-variance)
MachUp = Mach*(1.0+variance)
alphaLow = alpha-0.25
alphaUp = alpha+0.25
inFileDOE = 'LHS9_100.txt'
doe = mt.read_tabulated_data_without_header(inFileDOE)
lb = np.array([MachLow, alphaLow, 0.04343078, 0.0900427, 0.0570076, 0.08289899, -0.06762751, -0.13041535, -0.02843321])
ub = np.array([MachUp, alphaUp, 0.08343078, 0.1900427, 0.1570076, 0.18289899, 0.03237249, -0.03041535, 0.07156679])
zTE = 0.005
alt = 10000
yplus = 1.0
gridScaleL = 1.0
gridScaleH = 4.0
outputFile = inFileDOE[:-4] + '_CFD.txt'
norm = mt.Normalization(lb,ub)
xDOE = norm.denormalize(doe)
case = 0
fid = open(outputFile, 'wt')
fid.write('Mach\talpha\t')
for i in range(len(lb)-2):
fid.write('A%d\t'%(i+1))
#fid.write('clHigh\tcdHigh\tcmHigh\tclLow\tcdLow\tcmLow\tLDhigh\tLDlow\tthickness\n')
fid.write('cl\tcd\tcm\ttc\n')
fid.close()
for i, xx in enumerate(xDOE):
M = xx[0]
a = xx[1]
fc = cfd.flight_conditions.FlightConditions(M, alt)
af = MyTools.airfoil.airfoil.cst_x(xx[2:], 101)
af.set_trailing_edge(zTE)
tc = af.thickness
try:
# case += 1
# clH,cdH,cmH, gs = cfd.run_analysis(af, fc, a, yplus, gridScaleH, case)
case += 1
clL,cdL,cmL, gs = cfd.run_analysis(af, fc, a, yplus, gridScaleL, case)
fid = open(outputFile, 'at')
fid.write('%.6f\t%.6f\t'%(M,a))
for _x in xx[2:]:
fid.write('%.8f\t'%_x)
#fid.write('%.8f\t%.8f\t%.8f\t%.8f\t%.8f\t%.8f\t%.8f\t%.8f\t%.6f\n'%(clH,cdH,cmH,clL,cdL,cmL,clH/cdH,clL/cdL,tc))
fid.write('%.8f\t%.8f\t%.8f\t%.8f\n'%(clL,cdL,cmL,tc))
fid.close()
except IOError:
case += 1
fid = open(outputFile, 'at')
fid.write('%.6f\t%.6f\t'%(M,a))
for _x in xx[2:]:
fid.write('%.8f\t'%_x)
fid.write('calculation failed\n')
fid.close()
