OC.set_humidity(0.) nsect=50 wing_param=Wing_param('test_param',geom_type='Elliptic',n_sect=nsect) wing_param.set_distrib_type('cos_law') wing_param.build_wing() wing_param.set_value('span',40.) wing_param.set_value('root_chord',4.) wing_param.set_value('root_height',0.0) wing_param.set_value('tip_height',0.0) wing_param.build_linear_airfoil(OC, AoA0=0., Cm0=-0.1, set_as_ref=True) wing_param.build_airfoils_from_ref() wing_param.update() airfoils=wing_param.get_linked_airfoils() Cla=airfoils[24].ClAlpha(0.0,0.3) print "Cla=",Cla #list_file = ['SimpleRect_3.00E-01.dat','SimpleRect_6.00E-01.dat','SimpleRect_8.00E-01.dat'] list_file = ['Elliptic_2.00E-01.dat'] e=0.70 AR = wing_param.get_AR() print 'AR=',AR for i,file_name in enumerate(list_file): fid=open(file_name,'r') lines=fid.readlines() fid.close()