def run_lowRe():
#af = airfoil.naca4(12,2,30)
af = airfoil.read_txt('E:\\codes\\rae2822.txt')
af.display()
#af.read_txt(r'E:\laptop_sync\1. Projects\RENN\airfoil design\AG24new.txt')
# result = af.get_X_polar(0.02,0.355e6,[0,16,2.0],nIter=100)
fc = FlightConditions(22.,0,0,0.24)
solver = CFDsolver(af,fc,1.0,mesh='O')
solver.fluent.residuals['energy']=1e-6
solver.fluent.relaxationFactor['xvelocity'] = 1e-3
solver.mesh._airfoilPts = 75
solver.mesh._interiorPts = 75
solver.mesh._dsTE = solver.mesh._dsWall
solver.mesh._dsLE = 2e-3
solver.mesh._growthRate = 1.2
solver.create_mesh()
alpha = array([-10.,-5,0,5,10,12,14,16,18])
result = solver.run_for_multiple_aoa(alpha,turbulenceModel='SA')
for a,cl,cd,cm in zip(result.alpha,result.cl,result.cd,result.cm):
print a,'\t',cl,'\t',cd,'\t',cm
#ax3.grid(True,which='major',linestyle='-')
ax4.hold(True)
#ax4.grid(True,which='major',linestyle='-')
ax2.set_xlabel('Angle of attack, deg')
ax2.set_ylabel('Lift coefficient')
ax3.set_xlabel('Drag coefficient')
ax3.set_ylabel('Lift coefficient')
ax4.set_xlabel('Angle of attack, deg')
ax4.set_ylabel('Moment coefficient')
ax3.axis([0,0.05,-1,2])
linetype = ['k-.','k:','k--','k.']
ax1.axis('equal')
for i,name in enumerate(afName):
af = airfoil.read_txt(path1+'\\'+name)
pol = af.get_xfoil_polar(0.2,3e6,[-10,20,0.5],nIter=100)
ax1.plot(af.pts[:,0],af.pts[:,1]-0.2*i,linetype[i],label='airfoil %d'%(i+1),lw=1.5)
ax2.plot(pol.alpha,pol.cl,linetype[i],label='airfoil %d'%(i+1))
ax3.plot(pol.cd,pol.cl,linetype[i],label='airfoil %d'%(i+1))
ax4.plot(pol.alpha,pol.cm,linetype[i],label='airfoil %d'%(i+1))
print '%.4f '%af.thickness + '%.4f '%af.camber + '%.4f '%af.thicknessLocation + '%.4f '%af.camberLocation
ax2.legend(loc='lower right')
ax3.legend(loc='lower right')
plt.show()
