def calculate_bounds():
X = np.array([0.14391813, 0.18778261, 0.14634264, 0.15348147, 0.15107265, -0.09014438, -0.05862712, -0.03488944, -0.01428362, 0.03831908])
lb = X - np.array([0.01, 0.05, 0.05, 0.05, 0.00, 0.05, 0.05, 0.05, 0.05, 0.05])
ub = X + np.array([0.05, 0.05, 0.05, 0.05, 0.05, 0.01, 0.05, 0.05, 0.05, 0.00])
af1 = airfoil.cst(lb[0:5],ub[5:10])
af1.plot()
af2 = airfoil.cst(ub[0:5],lb[5:10])
af2.plot()
fc = cfd.FlightConditions(22.0,0.0,0,0.24)
result = aero_analysis(af1,fc,'thin.txt')
result = aero_analysis(af2,fc,'thick.txt')
def tmp_cst_plot():
Au = [0.120718,0.135291,0.174915,0.142468]
Al = [-0.120718,-0.150704,-0.176010,-0.040013]
af = airfoil.cst(Au,Al)
print af.thickness
af.plot()
def calc_airfoil(name,polarPath):
#Au = ny.array([0.178551,0.273254,0.268906,0.226346])
#Al = ny.array([-0.178551,-0.101338,-0.255260,-0.043527])
#Au = ny.array([0.1920,0.2887,0.2844,0.2304])
#Al = ny.array([-0.1920,-0.0859,-0.2398,-0.0255])
path = paths.CFD_paths()
landing = Flight_conditions(0.0,60.0)
#af = cst(Au,Al)
#af = Airfoil()
#af.read_airfoil_txt(name)
#af.read_txt(name)
#af.radius_LE=[]
af = cst([0.1839,0.3790,0.2712,0.1635],[-0.1839,-0.0493,-0.2190,-0.0225])
polarPath = 'optimum-polar.txt'
af.create_af_CAT(save = path.file_igs)
Airfoil_mesh(path,landing)
Airfoil_mesh.yplus_wall = 1.0
fluent = Solver(path,landing)
fluent.turb_model = 'ke-realizable'
#alphaSeq = ny.linspace(0,20,21)
#alphaSeq = ny.linspace(0,10,5)
alphaSeq = ny.linspace(0,20,21)#ny.array([10.0,12,14,16,18])
for alpha in alphaSeq:
fluent.run_fluent(alpha)
af.polar.Re = landing.Re
af.polar.M = landing.Mach
af.polar.Mach = landing.Mach
af.polar.alpha = fluent.alpha
af.polar.cl = fluent.cl
af.polar.cd = fluent.cd
af.polar.cm = fluent.cm
#af.write_polar_txt(r'D:\3. Projects\afOpt\results\af_GA20120716\landingCFDpolar_01_.pol')
af.write_polar_txt(polarPath)
def run_test1():
A = np.array([0.15225392, 0.17285363, 0.15722004, 0.13938069,-0.08884681, -0.05170833, -0.01974148, 0.02985025])
# A[3] += -0.04
# A[7] += 0.04
af = airfoil.cst(A[0:4],A[4:8])
af.plot()
fc = cfd.FlightConditions(22.0,0.0,0,0.24)
result = aero_analysis(af,fc,'testPolar.txt')
def _obj(x,*args):
up,lo = args
Au = x[0:5]
Al = x[5:10]
afcst = airfoil.cst(Au,Al)
sqErr = 0.0
for i,pt in enumerate(up[:,0]):
sqErr += (afcst.upCurve(pt) - up[i,1])**2.0
for i,pt in enumerate(lo[:,0]):
sqErr += (afcst.loCurve(pt) - lo[i,1])**2.0
return sqErr
def _err(x,*args):
up,lo = args
Au = x[0:5]
Al = x[5:10]
afcst = airfoil.cst(Au,Al)
upErr = zeros(len(up))
loErr = zeros(len(lo))
for i,pt in enumerate(up[:,0]):
upErr[i] = afcst.upCurve(pt) - up[i,1]
for i,pt in enumerate(lo[:,0]):
loErr[i] = (afcst.loCurve(pt) - lo[i,1])
return upErr, loErr
def _upd_cst(self,x,_norm=True):
if _norm:
x = denormalize(x,self.lb,self.ub)
n = len(x)
if n%2==0:
Au = x[:n/2]
Al = x[n/2:]
else:
Au = x[:int(n/2)+1]
Al = hstack([-x[0],x[int(n/2)+1:]])
self.af = Af.cst(Au,Al,25,'cos')
self.thickness = self.af.thickness
def run_baseline():
#X = np.array([0.14391813, 0.18778261, 0.14634264, 0.15348147, 0.15107265, -0.09014438, -0.05862712, -0.03488944, -0.01428362, 0.03831908])
#X = np.array([0.1639, 0.2078, 0.1663, 0.1629, 0.1511, -0.1049, -0.0548, -0.0149, -0.0009, 0.0383])
X = np.array([0.1439, 0.1878,0.1463,0.1535,0.1511,-0.0901,-0.0586,-0.0349,-0.0143,0.0383])
fc = cfd.FlightConditions(22.0,0.0,0,0.24)
fid = open('RENNbaseline.txt','wt')
fid.write('Au0\tAu1\tAu2\tAu3\tAu4\tAl0\tAl1\tAl2\tAl3\tAl4\tLDmax\talphaLDmax\tClmax\talphaClmax\tCdAtLDmax\tthickness\n')
fid.close()
#designs = read_doe(pathDOE)
#for i,design in enumerate(designs):
af = airfoil.cst(X[0:5],X[5:10])
result = aero_analysis(af, fc, 'tmp1z.txt')
write_output(X,result,'RENNbaseline.txt')
def test_plot_airfoil():
af1 = airfoil.Airfoil()
af1.read_txt('GA37A315.txt')
Au = [0.1823,0.3380,0.2650,0.2016]
Al = [-0.1823,-0.0708,-0.1885,-0.0384]
af2 = airfoil.cst(Au,Al)
rslt1 = af1.get_X_polar(0.18,4.4e6,[-10,20,1.0])
rslt2 = af2.get_X_polar(0.18,4.4e6,[-10,20,1.0])
alpha1 = [0,2,3,4,5,6,7,8,9,10,11,12,13,14,15,18,19,20]
cl1 = [0.243296,0.453613,0.558244,0.661459,0.763304,0.859225,0.951732,1.04177,1.12103,1.19799,1.26788,1.32786,1.38623,1.41998,1.42465,1.23664,1.18999,1.17667]
alpha2 = [0,1,2,5,7,8,12,13,14,15,16,17,18,19,20]
cl2 = [0.264347,0.372483,0.481921,0.801596,0.998552,1.09719,1.41826,1.46123,1.52317,1.54066,1.4781,1.35913,1.31233,1.27969,1.26525]
print af2.thickness
af1.analyze_geometry()
print af1.thickness
plt.figure(1)
plt.grid(True)
plt.hold(True)
plt.plot(af1.coord[:,0],af1.coord[:,1],'b-')
plt.plot(af2.coord[:,0],af2.coord[:,1],'r*-')
plt.legend(['Baseline','Optimum'])
plt.figure(2)
plt.grid(True)
plt.hold(True)
plt.plot(rslt1.cd,rslt1.cl,'b-')
plt.plot(rslt2.cd,rslt2.cl,'r*-')
plt.axis([0.002,0.012,-0.5,1.0])
plt.legend(['Baseline','Optimum'])
plt.xlabel('drag coefficient')
plt.ylabel('lift coefficient')
plt.figure(3)
plt.grid(True)
plt.hold(True)
#plt.plot(rslt1.alpha,rslt1.cl,'b-')
plt.plot(alpha1,cl1,'b-')
#plt.plot(rslt2.alpha,rslt2.cl,'r-')
plt.plot(alpha2,cl2,'r*-')
plt.axis([0,20,0,1.8])
#plt.legend(['baseline-low','baseline-high','optimum-low','optimum-high'],'lower right')
plt.legend(['Baseline','Optimum'],'lower right')
plt.show()
def run_full_table_analysis(wdir):
X,lb,ub,fc = get_initial_data()
pathDOE = os.getcwd() + '\\' + wdir + '\\1. input.txt'
pathOutput = os.getcwd() + '\\' + wdir + '\\2. outputAero.txt'
clcruise = 0.4
fid = open(pathOutput,'wt')
fid.write('Au0\tAu1\tAu2\tAu3\tAu4\tAl0\tAl1\tAl2\tAl3\tAl4\tLDmax\talphaLDmax\tClmax\talphaClmax\tCdAtLDmax\tLD32max\tthickness\tcdcruise\n')
fid.close()
#designs = read_doe(pathDOE)
designs = read_tabulated_data_without_header(pathDOE)
for i,design in enumerate(designs):
design = denormalize(design,lb,ub)
af = airfoil.cst(design[0:5],design[5:10])
filename = wdir + 'polar_%d.txt'%(i+1)
result = aero_analysis(af, fc, filename)
write_output(design,result,pathOutput,clcruise)
af.write_txt(wdir + 'coordinates_%d.txt'%(i+1))
def cst_fit():
af = airfoil.Airfoil()
af.read_txt(r'C:\Users\Maxim\Dropbox\2. projects\VCM\transonic airfoil\rae2822.txt',afType=2)
#af.read_txt(r'D:\laptop_sync\1. Projects\RENN\airfoil design\AG24new.txt')
#af.read_txt('pb092_closed.txt')
af.coord[:,1] = af.coord[:,1] - af.coord[:,0]*0.001868
af.separate_coordinates()
af.plot()
up, lo = af.upPts, af.loPts
args1 = up,lo
def _obj(x,*args):
up,lo = args
Au = x[0:5]
Al = x[5:10]
afcst = airfoil.cst(Au,Al)
sqErr = 0.0
for i,pt in enumerate(up[:,0]):
sqErr += (afcst.upCurve(pt) - up[i,1])**2.0
for i,pt in enumerate(lo[:,0]):
sqErr += (afcst.loCurve(pt) - lo[i,1])**2.0
return sqErr
def _err(x,*args):
up,lo = args
Au = x[0:5]
Al = x[5:10]
afcst = airfoil.cst(Au,Al)
upErr = zeros(len(up))
loErr = zeros(len(lo))
for i,pt in enumerate(up[:,0]):
upErr[i] = afcst.upCurve(pt) - up[i,1]
for i,pt in enumerate(lo[:,0]):
loErr[i] = (afcst.loCurve(pt) - lo[i,1])
return upErr, loErr
bnds = ((0.0,1.0),(-0.3,1.0),(-0.3,1.0),(-0.3,1.0),(-0.3,1.0),(-1.0,0.0),(-1.0,0.3),(-1.0,0.3),(-1.0,0.3),(-1.0,0.3))
rslt = minimize(_obj,x0=0.1*ones(10),bounds=bnds,method='SLSQP',args=args1)
xnew = rslt.x
upErr, lowErr = _err(xnew,up,lo)
#xnew[:4] += +0.075
#xnew[4:] += -0.075
print xnew
#xnew += 0.05
afnew = airfoil.cst(xnew[0:5],xnew[5:10])
print afnew.thickness
fid = open('GA37A315cst.txt','wt')
for xx in xnew:
fid.write('%.8f\t'%xx)
fid.close()
fig = plt.figure(1)
ax1 = fig.add_subplot(211)
ax2 = fig.add_subplot(212)
ax1.hold(True)
ax1.set_title(af.name)
ax2.set_title('Fit error')
ax1.plot(af.coord[:,0],af.coord[:,1],'k-')
ax1.plot(afnew.coord[:,0],afnew.coord[:,1],'r.-')
ax1.axis('equal')
ax1.legend(['Original Airfoil','CST fit'])
ax2.hold(True)
ax2.plot(up[:,0],upErr,'ks-',markevery=3)
ax2.plot(lo[1:,0],lowErr[1:],'k^-',markevery=3)
ax2.set_ylabel('error')
ax2.legend(['Upper curve','Lower curve'],'lower left')
plt.show()
def _upd_cst(self,x):
#x = denormalize(x,self.lb,self.ub)
Au = x[:4]
Al = array([-x[0],x[4],x[5],x[6]])
self.af = Af.cst(Au,Al)
self.thickness = self.af.thickness