def testFcn():
path = paths.CFD_paths('GA_opt')
cruise = Flight_conditions(1500, 48.92)
af = Airfoil()
af.CST_airfoil(ny.array([0.178551,0.273254,0.268906,0.226346]),ny.array([-0.178551,-0.101338,-0.255260,-0.043527]))
af.write_airfoil_txt('optAirfoil.dat')
af.create_af_CAT(save = path.file_igs)
Airfoil_mesh(path,cruise)
Airfoil_mesh.yplus_wall = 1.0
fluent = Solver(path,cruise)
fluent.turb_model = 'ke-realizable'
for alpha in range(10, 21, 2):
fluent.run_fluent(alpha)
af.polar.Re = cruise.Re
af.polar.M = cruise.Mach
af.polar.alpha = fluent.alpha
af.polar.CL = fluent.cl
af.polar.CD = fluent.cd
af.polar.CM = fluent.cm
#af.calc_Jpolar(0.1463,2999951,ny.array([-2,20,2.]))
af.write_polar_txt(r'D:\3. Projects\afOpt\experimental data\GAopt.pol')
#def batch_calculation():
designs = open(r'D:\3. Projects\afOpt\results\CFD_20120719\Designs.txt','rt')
Au = ny.zeros([4,1])
Al = ny.zeros([4,1])
lines = designs.readlines()
designs.close()
landing = Flight_conditions(0, 32.5)
path = paths.CFD_paths()
results = r'D:\3. Projects\afOpt\results\CFD_20120719'
for N,line in enumerate(lines):
path.set_name(('DoE_%d'%N))
segLine = line.split()
Au[0] = float(segLine[0])
Au[1] = float(segLine[1])
Au[2] = float(segLine[2])
Au[3] = float(segLine[3])
Al[0] = -float(segLine[0])
Al[1] = float(segLine[4])
Al[2] = float(segLine[5])
Al[3] = float(segLine[6])
af = Airfoil()
af.name = ('DoE %d'%N)
af.CST_airfoil(Au,Al)
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.array([10, 12, 14, 16, 18, 20])
for alpha in alphaSeq:
fluent.run_fluent(alpha)
af.polar.Re = landing.Re
af.polar.M = landing.Mach
af.polar.alpha = fluent.alpha
af.polar.cl = fluent.cl
af.polar.cd = fluent.cd
af.polar.cm = fluent.cm
af.write_airfoil_txt(('%s\\airfoil_%d_coord.dat'%(results,N)))
af.write_polar_txt(('%s\\airfoil_%d.pol'%(results,N)))