Patm = 101325.#Pa
rho = 1.225#kg.m-3
c = numpy.sqrt(1.4*Patm/rho)
Mach = 0.17
airspeed = c*Mach
run_case(filename,
wake_length=20.,
alpha=[x[7]],
beta=[0.],
v=25.,
rho=rho,
P=Patm,
Mach=Mach,
origin=[0.,0.,0.],
wingspan=2.*x[0],
ref_chord=1.,
Sref=10.,
method=0,
farfield_dist=50.,
velorder=1)
fid = open('wing_polar.dat')
lines = fid.readlines()
fid.close()
[_,Cl,Cd] = [eval(word) for word in lines[0].split()]
print Cl,10000.*Cd
dakota_utils.write_outputs(sys.argv[2],[Cd,0.5-Cl],['Cd','Cl'])
import sys
import numpy
import dakota_utils #--> le module a creer
def my_func(x):
return x[0]**2+x[1]**2
def constraint(x):
return x[0]-2.
x,varnames=dakota_utils.read_input(sys.argv[1])
fval = my_func(x)
cstr = constraint(x)
dakota_utils.write_outputs(sys.argv[2],[fval,cstr],['my_function','my_constraint'])
