def run_apame():
# compute flight conditions
r=287.058 #J.kg-1.K-1
Patm = 101325.#Pa
rho = 1.225#kg.m-3
mu=1.5e-5
T = Patm/(r*rho)
Tc = T-273.15
print "T=",T
Re=5.e5
airspeed = Re*mu/rho
print "Airspeed=",airspeed*3.6
# list of alpha and beta to compute
alpha_list = numpy.linspace(-10.,10.,21)
beta_list = numpy.zeros(21)
run_case('optimized_wing.vtp',
wake_length=10.,
alpha=alpha_list,
beta=beta_list,
v=airspeed,
rho=rho,
P=Patm,
Mach=0.,
origin=[0.,0.,0.],
wingspan=10.,
ref_chord=1.,
Sref=10.,
method=0,
farfield_dist=50.,
velorder=1)
def run_apame(nb_angles):
# compute flight conditions
r=287.058 #J.kg-1.K-1
Patm = 101325.#Pa
rho = 1.225#kg.m-3
mu=1.5e-5
T = Patm/(r*rho)
Tc = T-273.15
print "T=",T
airspeed = Re*mu/rho
print "Airspeed=",airspeed*3.6
# list of alpha and beta to compute
span_angles=float((nb_angles-1)//2)
alpha_list = numpy.linspace(-span_angles,span_angles,nb_angles)
beta_list = numpy.zeros(nb_angles)
run_case('initial'+str(nb)+'.vtp',
wake_length=10.,
alpha=alpha_list,
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)
def run_apame():
# compute flight conditions
r = 287.058 # J.kg-1.K-1
Patm = 101325.0 # Pa
rho = 1.225 # kg.m-3
mu = 1.5e-5
T = Patm / (r * rho)
Tc = T - 273.15
print "T=", T
airspeed = Re * mu / rho
print "Airspeed=", airspeed * 3.6
# list of alpha and beta to compute
alpha_list = numpy.linspace(-5.0, 5.0, 11)
beta_list = numpy.zeros(11)
run_case(
"output.vtp",
wake_length=10.0,
alpha=alpha_list,
beta=beta_list,
v=airspeed,
rho=rho,
P=Patm,
Mach=0.0,
origin=[0.0, 0.0, 0.0],
wingspan=10.0,
ref_chord=1.0,
Sref=Sref,
method=0,
farfield_dist=50.0,
velorder=1,
)
T = Patm / (r * rho)
Tc = T - 273.15
print "T=", T
Re = 5.0e5
airspeed = Re * mu / rho
print "Airspeed=", airspeed * 3.6
# list of alpha and beta to compute
alpha_list = numpy.linspace(-10.0, 10.0, 10)
beta_list = numpy.zeros(10)
run_case(
"naca0012.vtp",
wake_length=10.0,
alpha=alpha_list,
beta=beta_list,
v=airspeed,
rho=rho,
P=Patm,
Mach=0.0,
origin=[0.0, 0.0, 0.0],
wingspan=10.0,
ref_chord=1.0,
Sref=10.0,
method=0,
farfield_dist=50.0,
velorder=1,
)
rho = 1.225#kg.m-3
mu=1.5e-5
T = Patm/(r*rho)
Tc = T-273.15
print "T=",T
Re=5.e5
airspeed = Re*mu/rho
print "Airspeed=",airspeed*3.6
# list of alpha and beta to compute
alpha_list = numpy.zeros(1)
beta_list = numpy.zeros(1)
run_case('output.vtp',
wake_length=10.,
alpha=alpha_list,
beta=beta_list,
v=airspeed,
rho=rho,
P=Patm,
Mach=0.,
origin=[0.,0.,0.],
wingspan=10.,
ref_chord=1.,
Sref=10.,
method=0,
farfield_dist=50.,
velorder=1)
nv=21)
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
print "Re=",Re
print "airspeed=",airspeed*3.6
Sref=15.
Sw = (root_chord+tip_chord)*semi_span
print "Sw=",Sw
run_case(filename,
wake_length=20.,
alpha=[2.],
beta=[0.],
v=airspeed,
rho=rho,
P=Patm,
Mach=Mach,
origin=[0.,0.,0.],
wingspan=2.*semi_span,
ref_chord=root_chord,
Sref=Sref,
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
