コード例 #1
0
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)
コード例 #2
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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)
コード例 #3
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ファイル: myfunc.py プロジェクト: ymerillac/Optim_INSA_5GMM
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,
    )
コード例 #4
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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,
)
コード例 #5
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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)
コード例 #6
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           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
コード例 #7
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ファイル: test_cf.py プロジェクト: ymerillac/Optim_INSA_5GMM
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