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()
