def my_func(M,P,T,aoa,span,tip_chord):
chord[1] = tip_chord
mesh_utils.write_wing_file(M,P,T,chord,span,n_sections,n_naca_pts)
NACA.create_wing('current_wing','output')
run_apame(aoa)
fid = open('output_polar.dat','r')
nb_lines=0
while fid.readline():
nb_lines+=1
if nb_lines==0:
raise TypeError("Empty file")
fid.close()
fid = open('output_polar.dat','r')
# revenir au debut
alpha=numpy.zeros(nb_lines)
cx=numpy.zeros(nb_lines)
cz=numpy.zeros(nb_lines)
for i in xrange(nb_lines):
tmp=fid.readline()
tmp=tmp.split()
alpha[i]=float(tmp[0])
cx[i]=float(tmp[2])
cz[i]=float(tmp[1])
fid.close()
ind = cx.argmin()
Cf = 0.0583/Re**0.2
Sw = (chord[0]+chord[1])*span/2.
Cd_friction = Sw/Sref*Cf
return min(cx)+Cd_friction,cz[ind]
def my_func(M, P, T, span, tip_chord):
chord[1] = tip_chord
mesh_utils.write_wing_file(M, P, T, chord, span, n_sections, n_naca_pts)
NACA.create_wing("current_wing", "output")
run_apame()
fid = open("output_polar.dat", "r")
nb_lines = 0
while fid.readline():
nb_lines += 1
if nb_lines == 0:
raise TypeError("Empty file")
fid.close()
fid = open("output_polar.dat", "r")
# revenir au debut
alpha = numpy.zeros(nb_lines)
cx = numpy.zeros(nb_lines)
cz = numpy.zeros(nb_lines)
finesse = numpy.zeros(nb_lines)
Cf = 0.0583 / Re ** 0.2
Sw = (chord[0] + chord[1]) * span / 2.0
Cd_friction = Sw / Sref * Cf
for i in xrange(nb_lines):
tmp = fid.readline()
tmp = tmp.split()
alpha[i] = float(tmp[0])
cx[i] = float(tmp[2]) + Cd_friction
cz[i] = float(tmp[1])
finesse[i] = cz[i] / cx[i]
fid.close()
return max(finesse)
def my_func(X):
chord=[1.,1.]
M=X[0:2]
P=X[2:4]
T=X[4:6]
alpha=X[6]
span=X[7]
chord[1]=X[8]
n_sections=31
n_naca_pts=50
Sref=10.
Re=5.e5
mesh_utils.write_wing_file(M,P,T,chord,span,n_sections,n_naca_pts)
NACA.create_wing('current_wing','output')
run_apame(alpha)
fid = open('output_polar.dat','r')
nb_lines=0
while fid.readline():
nb_lines+=1
if nb_lines==0:
raise TypeError("Empty file")
fid.close()
fid = open('output_polar.dat','r')
# revenir au debut
alpha=numpy.zeros(nb_lines)
cx=numpy.zeros(nb_lines)
cz=numpy.zeros(nb_lines)
for i in xrange(nb_lines):
tmp=fid.readline()
tmp=tmp.split()
alpha[i]=float(tmp[0])
cx[i]=float(tmp[2])
cz[i]=float(tmp[1])
fid.close()
#f = interpolate.interp1d(numpy.array(cz), numpy.array(cx), kind='cubic')
#print 'DRAG >>> ', min(cx)
#cx=f(0.5)
ind = cx.argmin()
Cf = 0.0583/Re**0.2
Sw = (chord[0]+chord[1])*span/2.
Cd_friction = Sw/Sref*Cf
print 'DRAG >>> ', cx+Cd_friction
cx_tab[k]=cx+Cd_friction
contrainte_tab[k]=0.5-cz
k=k+1
return cx+Cd_friction#,cz[ind]
beta=beta_list,
v=airspeed,
rho=rho,
P=Patm,
Mach=0.,
origin=[0.,0.,0.],
wingspan=10.,
ref_chord=1.,
Sref=Sref,
method=0,
farfield_dist=50.,
velorder=1)
if nb==8415:
nb_angles=11
M=[0.08,0.08]
P=[0.4,0.4]
T=[0.15,0.15]
elif nb==12:
nb_angles=21
M=[0.0,0.0]
P=[0.4,0.4]
T=[0.12,0.12]
mesh_utils.write_wing_file(M,P,T,chord,span,n_sections,n_naca_pts)
NACA.create_wing('current_wing','initial'+str(nb))
run_apame(nb_angles)