xopt = np.transpose(np.vstack([x1,x2])) print neval print i out.write_array(itr,'itr') out.write_array(x1,'x1') out.write_array(x2,'x2') out.write_array(fval,'f') out.write_array(errorVal,'err') out.write_array(offset,'dg') out.write_array(g1val,'g1') out.write_array(g2hval,'g2h') out.write_array(g2lval,'g2l') out.write_array(g2aval,'g2new') out.write_array(g3val,'g3') out.close() delta = 0.1 x = np.arange(0, 10+delta, delta) y = np.arange(0, 10+delta, delta) X, Y = np.meshgrid(x, y)
def plot_result_af():
x0 = array([0.1670, 0.3340, 0.2601, 0.1971, -0.0713, -0.1951, -0.0498])
x1 = [0.1839,0.3520,0.2512,0.1835,-0.0493,-0.2190,-0.0225]
x2 = [0.1729,0.3482,0.2707,0.2045,-0.0774,-0.1563,-0.0498]
rsltFile = SaveTextData('af_sub_20141207.txt')
def print_polar(pol):
print '-->'
for i in range(len(pol.alpha)):
print '%.2f\t%.6f\t%.6f\t%.6f'%(pol.alpha[i],pol.cl[i],pol.cd[i],pol.cm[i])
aa = AirfoilAnalysis()
aa._upd_cst(x0,False)
crd0 = copy(aa.af.coord)
pol0 = aa._run_fluent(x0,False)
pol0x = aa.af.get_X_polar(aa.Mldg,aa.landing.Re,alphaSeq=[-10,10,1])
print_polar(pol0)
print_polar(pol0x)
aa._upd_cst(x1,False)
crd1 = copy(aa.af.coord)
pol1 = aa._run_fluent(x1,False)
pol1x = aa.af.get_X_polar(aa.Mldg,aa.landing.Re,alphaSeq=[-10,10,1])
print_polar(pol1)
print_polar(pol1x)
aa._upd_cst(x2,False)
crd2 = copy(aa.af.coord)
pol2 = aa._run_fluent(x2,False)
pol2x = aa.af.get_X_polar(aa.Mldg,aa.landing.Re,alphaSeq=[-10,10,1])
print_polar(pol0)
print_polar(pol0x)
print_polar(pol1)
print_polar(pol1x)
print_polar(pol2)
print_polar(pol2x)
rsltFile.write_array(crd0[:,0],'x0')
rsltFile.write_array(crd0[:,1],'y0')
rsltFile.write_array(crd1[:,0],'x1')
rsltFile.write_array(crd1[:,1],'y1')
rsltFile.write_array(crd2[:,0],'x2')
rsltFile.write_array(crd2[:,1],'y2')
rsltFile.write_array(pol0x.cd,'cd0x')
rsltFile.write_array(pol1x.cd,'cd1x')
rsltFile.write_array(pol2x.cd,'cd2x')
rsltFile.write_array(pol0x.cl,'cl0x')
rsltFile.write_array(pol1x.cl,'cl1x')
rsltFile.write_array(pol2x.cl,'cl2x')
rsltFile.write_array(pol0.alpha,'a0')
rsltFile.write_array(pol1.alpha,'a1')
rsltFile.write_array(pol2.alpha,'a2')
rsltFile.write_array(pol0.cl,'cl0')
rsltFile.write_array(pol1.cl,'cl1')
rsltFile.write_array(pol2.cl,'cl2')
rsltFile.close()
plt.figure(1)
plt.hold(True)
plt.grid(True)
plt.plot(crd0[:,0],crd0[:,1],'k--',linewidth=2)
plt.plot(crd1[:,0],crd1[:,1],'r-',linewidth=2)
plt.plot(crd2[:,0],crd2[:,1],'b:',linewidth=2)
plt.legend(['baseline','GVFM','VCM'])
plt.figure(2)
plt.hold(True)
plt.grid(True)
plt.axis([0.002, 0.012, -0.5, 1.0])
plt.plot(pol0x.cd, pol0x.cl, 'ks--',linewidth=2)
plt.plot(pol1x.cd, pol1x.cl, 'ro-',linewidth=2)
plt.plot(pol2x.cd, pol2x.cl, 'b^:',linewidth=2)
plt.xlabel('Drag coefficient')
plt.ylabel('Lift coefficient')
plt.legend(['baseline','GVFM','VCM'],'lower right')
plt.figure(3)
plt.hold(True)
plt.grid(True)
plt.axis([0,20,0,1.8])
plt.plot(pol0.alpha, pol0.cl, 'ks--',linewidth=2)
plt.plot(pol1.alpha, pol1.cl, 'ro-',linewidth=2)
plt.plot(pol2.alpha, pol2.cl, 'b^:',linewidth=2)
plt.xlabel('Angle of attack, deg')
plt.ylabel('Lift coefficient')
plt.legend(['baseline','GVFM','VCM'],'lower right')
plt.show()