def __init_Newton_Raphson(self):
N=self.get_N()
iAoA0= zeros(N)
self.__NRPb = NewtonRaphsonProblem(iAoA0, self.comp_R, self.comp_dpR_dpiAoA)
self.__NRPb.set_relax_factor(0.99)
self.__NRPb.set_stop_residual(1.e-9)
self.__NRPb.set_max_iterations(100)
def __init_Newton_Raphson(self):
W0 = numpy.zeros(self.__N + 1)
self.__NRPb = NewtonRaphsonProblem(W0, self.comp_R_TCl,
self.comp_dpR_TCl_dpW)
self.__NRPb.set_relax_factor(0.99)
self.__NRPb.set_stop_residual(1.e-9)
self.__NRPb.set_max_iterations(100)
def __init_Newton_Raphson(self):
N = self.get_N()
iAoA0 = zeros(N)
self.comp_R(iAoA0)
self.comp_dpR_dpiAoA(iAoA0)
self.__NRPb = NewtonRaphsonProblem(iAoA0,self.comp_R,self.comp_dpR_dpiAoA,verbose = self.__verbose)
self.__NRPb.set_relax_factor(0.99)
self.__NRPb.set_stop_residual(1.e-9)
self.__NRPb.set_max_iterations(100)
def __init_Newton_Raphson(self):
W0= numpy.zeros(self.__N+1)
self.__NRPb = NewtonRaphsonProblem(W0, self.comp_R_TCl, self.comp_dpR_TCl_dpW, verbose = self.__verbose)
self.__NRPb.set_relax_factor(0.99)
self.__NRPb.set_stop_residual(1.e-9)
self.__NRPb.set_max_iterations(100)
class DLLMTargetCl(DLLMSolver):
ERROR_MSG='ERROR in DLLMTargetCl.'
def __init__(self, tag, wing_param, OC, verbose = 0):
self.__verbose = verbose
DLLMSolver.__init__(self, tag, wing_param, OC, verbose = self.__verbose)
self.__N = self.get_wing_param().get_n_sect()
self.__ndv = self.get_wing_param().get_ndv()
self.__R_TCl = numpy.zeros(self.__N+1)
self.__dpR_TCl_dpW = numpy.zeros((self.__N+1,self.__N+1))
self.__dpR_TCl_dpchi = numpy.zeros((self.__N+1,self.__ndv))
self.__dpF_list_dpW = None
self.__target_Cl = 0.5
# initialize the Newton-Raphson problem
self.__NRPb = None
self.__init_Newton_Raphson()
# -- Accessors
def get_target_Cl(self):
return self.__target_Cl
def set_target_Cl(self, target):
self.__target_Cl = target
#-- Newton-Raphson related methods
def __init_Newton_Raphson(self):
W0= numpy.zeros(self.__N+1)
self.__NRPb = NewtonRaphsonProblem(W0, self.comp_R_TCl, self.comp_dpR_TCl_dpW, verbose = self.__verbose)
self.__NRPb.set_relax_factor(0.99)
self.__NRPb.set_stop_residual(1.e-9)
self.__NRPb.set_max_iterations(100)
def set_relax_factor(self, relax_factor):
self.__NRPb.set_relax_factor(relax_factor)
def set_stop_residual(self, residual):
self.__NRPb.set_stop_residual(residual)
def set_max_iterations(self, max_it):
self.__NRPb.set_max_iterations(max_it)
def set_method(self, method):
self.__NRPb.set_method(method)
#-- Residual Related method
def comp_R_TCl(self, W):
DLLMDirect = self.get_DLLMDirect()
DLLMPost = self.get_DLLMPost()
OC = self.get_OC()
iAoA = W[0:self.__N]
AoA = W[self.__N]
OC.set_AoA_rad(AoA)
R = DLLMDirect.comp_R(iAoA)
Cl = DLLMPost.comp_Cl()
self.__R_TCl[:self.__N] = R[:]
self.__R_TCl[self.__N] = Cl - self.__target_Cl
return self.__R_TCl
def comp_dpR_TCl_dpW(self, W):
DLLMDirect = self.get_DLLMDirect()
DLLMPost = self.get_DLLMPost()
OC = self.get_OC()
iAoA = W[0:self.__N]
AoA = W[self.__N]
OC.set_AoA_rad(AoA)
dpR_dpiAoA = DLLMDirect.comp_dpR_dpiAoA(iAoA)
dpCl_dpiAoA = DLLMPost.comp_dpCl_dpiAoA()
dpR_dpAoA = DLLMDirect.comp_dpR_dpAoA()
dpCl_dpAoA = DLLMPost.dpCl_dpAoA()
self.__dpR_TCl_dpW[0:self.__N,0:self.__N] = dpR_dpiAoA[:,:]
self.__dpR_TCl_dpW[self.__N,0:self.__N] = dpCl_dpiAoA[:]
self.__dpR_TCl_dpW[0:self.__N,self.__N] = dpR_dpAoA[:]
self.__dpR_TCl_dpW[self.__N,self.__N] = dpCl_dpAoA
return self.__dpR_TCl_dpW
def get_R(self):
return self.__R_TCl
def get_dpR_dpW(self):
return self.__dpR_TCl_dpW
def get_dpR_dpchi(self):
DLLMDirect = self.get_DLLMDirect()
DLLMPost = self.get_DLLMPost()
dpR_dpchi = DLLMDirect.get_dpR_dpchi()
dpCl_dpchi = DLLMPost.dpCl_dpchi()
self.__dpR_TCl_dpchi[:self.__N,:] = dpR_dpchi[:,:]
self.__dpR_TCl_dpchi[self.__N,:] = dpCl_dpchi[:]
return self.__dpR_TCl_dpchi
def get_dpF_list_dpW(self):
DLLMPost = self.get_DLLMPost()
dpF_list_dpiAoA = DLLMPost.get_dpF_list_dpiAoA()
dpF_list_dpAoA = DLLMPost.get_dpF_list_dpAoA()
dim = len(dpF_list_dpiAoA)
self.__dpF_list_dpW = numpy.zeros((dim,self.__N+1))
for i in xrange(dim):
self.__dpF_list_dpW[i,:self.__N] = dpF_list_dpiAoA[i,:]
self.__dpF_list_dpW[i,self.__N] = dpF_list_dpAoA[i]
return self.__dpF_list_dpW
def run_direct(self):
DLLMDirect = self.get_DLLMDirect()
# W0= numpy.zeros(self.__N+1)
# self.__NRPb.valid_jacobian(W0, iprint=True)
self.__NRPb.solve()
DLLMDirect.set_computed(True)
DLLMDirect.write_gamma_to_file()
DLLMDirect.comp_dpR_dpchi()
class DLLMTargetLift(DLLMSolver):
ERROR_MSG='ERROR in DLLMTargetLift.'
def __init__(self, tag, wing_param, OC):
DLLMSolver.__init__(self, tag, wing_param, OC)
self.__N = self.get_wing_param().get_n_sect()
self.__ndv = self.get_wing_param().get_ndv()
self.__R_TL = numpy.zeros(self.__N+1)
self.__dpR_TL_dpW = numpy.zeros((self.__N+1,self.__N+1))
self.__dpR_TL_dpchi = numpy.zeros((self.__N+1,self.__ndv))
self.__dpF_list_dpW = None
self.__target_Lift = 10000.
# initialize the Newton-Raphson problem
self.__NRPb = None
self.__init_Newton_Raphson()
# -- Accessors
def get_target_Lift(self):
return self.__target_Lift
def set_target_Lift(self, target):
self.__target_Lift = target
#-- Newton-Raphson related methods
def __init_Newton_Raphson(self):
W0= numpy.zeros(self.__N+1)
self.__NRPb = NewtonRaphsonProblem(W0, self.comp_R_TL, self.comp_dpR_TL_dpW)
self.__NRPb.set_relax_factor(0.99)
self.__NRPb.set_stop_residual(1.e-9)
self.__NRPb.set_max_iterations(100)
def set_relax_factor(self, relax_factor):
self.__NRPb.set_relax_factor(relax_factor)
def set_stop_residual(self, residual):
self.__NRPb.set_stop_residual(residual)
def set_max_iterations(self, max_it):
self.__NRPb.set_max_iterations(max_it)
def set_method(self, method):
self.__NRPb.set_method(method)
#-- Residual Related method
def comp_R_TL(self, W):
DLLMDirect = self.get_DLLMDirect()
DLLMPost = self.get_DLLMPost()
OC = self.get_OC()
iAoA = W[0:self.__N]
AoA = W[self.__N]
OC.set_AoA_rad(AoA)
R = DLLMDirect.comp_R(iAoA)
Lift = DLLMPost.comp_Lift()
self.__R_TL[:self.__N] = R[:]
self.__R_TL[self.__N] = Lift - self.__target_Lift
return self.__R_TL
def comp_dpR_TL_dpW(self, W):
DLLMDirect = self.get_DLLMDirect()
DLLMPost = self.get_DLLMPost()
OC = self.get_OC()
iAoA = W[0:self.__N]
AoA = W[self.__N]
OC.set_AoA_rad(AoA)
dpR_dpiAoA = DLLMDirect.comp_dpR_dpiAoA(iAoA)
dpLift_dpiAoA = DLLMPost.comp_dpLift_dpiAoA()
dpR_dpAoA = DLLMDirect.comp_dpR_dpAoA()
dpLift_dpAoA = DLLMPost.dpLift_dpAoA()
self.__dpR_TL_dpW[0:self.__N,0:self.__N] = dpR_dpiAoA[:,:]
self.__dpR_TL_dpW[self.__N,0:self.__N] = dpLift_dpiAoA[:]
self.__dpR_TL_dpW[0:self.__N,self.__N] = dpR_dpAoA[:]
self.__dpR_TL_dpW[self.__N,self.__N] = dpLift_dpAoA
return self.__dpR_TL_dpW
def get_R(self):
return self.__R_TL
def get_dpR_dpW(self):
return self.__dpR_TL_dpW
def get_dpR_dpchi(self):
DLLMDirect = self.get_DLLMDirect()
DLLMPost = self.get_DLLMPost()
dpR_dpchi = DLLMDirect.get_dpR_dpchi()
dpLift_dpchi = DLLMPost.dpLift_dpchi()
self.__dpR_TL_dpchi[:self.__N,:] = dpR_dpchi[:,:]
self.__dpR_TL_dpchi[self.__N,:] = dpLift_dpchi[:]
return self.__dpR_TL_dpchi
def get_dpF_list_dpW(self):
DLLMPost = self.get_DLLMPost()
dpF_list_dpiAoA = DLLMPost.get_dpF_list_dpiAoA()
dpF_list_dpAoA = DLLMPost.get_dpF_list_dpAoA()
dim = len(dpF_list_dpiAoA)
self.__dpF_list_dpW = numpy.zeros((dim,self.__N+1))
for i in xrange(dim):
self.__dpF_list_dpW[i,:self.__N] = dpF_list_dpiAoA[i,:]
self.__dpF_list_dpW[i,self.__N] = dpF_list_dpAoA[i]
return self.__dpF_list_dpW
def run_direct(self):
DLLMDirect = self.get_DLLMDirect()
# W0= numpy.zeros(self.__N+1)
# self.__NRPb.valid_jacobian(W0, iprint=True)
self.__NRPb.solve()
DLLMDirect.set_computed(True)
DLLMDirect.write_gamma_to_file()
DLLMDirect.comp_dpR_dpchi()
wing_param.convert_to_design_variable('tip_chord', (1., 2.))
wing_param.convert_to_design_variable('root_height', (1., 1.5))
wing_param.convert_to_design_variable('break_height', (0.8, 1.2))
wing_param.convert_to_design_variable('tip_height', (0.2, 0.5))
wing_param.build_linear_airfoil(OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
print wing_param
N = wing_param.get_n_sect()
iAoA0 = numpy.zeros(N)
DLLM = DLLMSolver('test', wing_param, OC)
NRPb = NewtonRaphsonProblem(iAoA0, DLLM.comp_R, DLLM.comp_dpR_dpiAoA)
NRPb.set_relax_factor(0.99)
NRPb.set_stop_residual(1.e-9)
NRPb.set_max_iterations(100)
iAoA = NRPb.solve()
DLLM.set_direct_computed()
print iAoA
DLLM.comp_dpR_dpchi()
dpRdpthetaY = DLLM.comp_dpR_dpthetaY()
print 'dpRdpthetaY=', dpRdpthetaY
print DLLM.get_iAoA()
class DLLMDirect:
"""
Direct solver for the lifting line wing model
"""
DEG_TO_RAD = numpy.pi/180.
RAD_TO_DEG = 180./numpy.pi
def __init__(self, LLW):
self.__LLW = LLW
self.__computed = False
self.__gamma_f_name = None
# initialize local variables
self.__init_local_variables()
# initialize the Newton-Raphson problem
self.__NRPb = None
self.__init_Newton_Raphson()
#-- Accessors
def get_tag(self):
return self.__LLW.get_tag()
def get_wing_param(self):
return self.__LLW.get_wing_param()
def get_airfoils(self):
return self.__LLW.get_airfoils()
def get_K(self):
return self.__LLW.get_K()
def get_dK_dchi(self):
return self.__LLW.get_dK_dchi()
def get_N(self):
return self.get_wing_param().get_n_sect()
def get_ndv(self):
return self.get_wing_param().get_ndv()
def get_OC(self):
return self.__LLW.get_OC()
def get_iAoA(self):
return self.__iAoA
def get_localAoA(self):
return self.__localAoA
def get_R(self):
return self.__R
def get_dpR_dpiAoA(self):
return self.__dpR_dpiAoA
def get_dpR_dpchi(self):
return self.__dpR_dpchi
def get_dplocalAoA_dpiAoA(self):
return self.__dplocalAoA_dpiAoA
def get_dplocalAoA_dpAoA(self):
return self.__dplocalAoA_dpAoA
def get_dplocalAoA_dpchi(self):
return self.__dplocalAoA_dpchi
def get_convergence_history(self):
"""
Accessor to the last computation convergence history as a list of residuals normalized by the first iteration residual.
"""
return self.__residuals_hist
def is_computed(self):
return self.__computed
#-- Setters
def set_computed(self, bool=True):
self.__computed = bool
def set_gamma_file_name(self, gamma_f_name):
self.__gamma_f_name = gamma_f_name
#-- Newton-Raphson related methods
def __init_Newton_Raphson(self):
N=self.get_N()
iAoA0= zeros(N)
self.__NRPb = NewtonRaphsonProblem(iAoA0, self.comp_R, self.comp_dpR_dpiAoA)
self.__NRPb.set_relax_factor(0.99)
self.__NRPb.set_stop_residual(1.e-9)
self.__NRPb.set_max_iterations(100)
def set_relax_factor(self, relax_factor):
self.__NRPb.set_relax_factor(relax_factor)
def set_stop_residual(self, residual):
self.__NRPb.set_stop_residual(residual)
def set_max_iterations(self, max_it):
self.__NRPb.set_max_iterations(max_it)
def set_method(self, method):
self.__NRPb.set_method(method)
#-- Computation related methods
def run(self):
self.__NRPb.solve()
self.set_computed(True)
self.write_gamma_to_file()
self.comp_dpR_dpchi()
def __init_local_variables(self):
# Initializing local variables for lifting line computations
# Residual variables
N=self.get_N()
ndv=self.get_ndv()
self.__R = zeros([N])
self.__dpR_dpiAoA = None
self.__dpR_dpchi = None
self.__dpR_dpthetaY = None
self.__dpR_dpAoA = None
# Angle of attack variables
self.__localAoA = zeros([N])
self.__dplocalAoA_dpiAoA = diag(ones([N])) # This is a constant matrix
self.__dplocalAoA_dpthetaY = diag(ones([N])) # This is a constant matrix
self.__dplocalAoA_dpAoA = ones(N)
self.__dplocalAoA_dpchi = zeros([N,ndv])
# Induced angle of attack variables
self.__iAoA = None
self.__iAoANew = None
self.__dpiAoAnew_dpchi = zeros([N,ndv])
self.__dpiAoAnew_dpiAoA = None
# Circulation variables
self.__gamma = zeros(N)
self.__dpgamma_dpiAoA = None
self.__dpgamma_dpthetaY = None
self.__dpgamma_dpAoA = None
self.__dpgamma_dplocalAoA = zeros([N,N])
self.__dpgamma_dpchi = zeros([N,ndv])
#-- Residual related methods
def comp_R(self, iAoA):
self.__iAoA = iAoA
self.__compute_localAoA()
self.__compute_gamma()
self.__compute_iAoAnew()
self.__R = self.__iAoA - self.__iAoANew
return self.__R
def comp_dpR_dpiAoA(self, iAoA):
N=self.get_N()
R=self.comp_R(iAoA)
# dplocalAoA_dpiAoA is a constant matrix, no need to compute it (self.__dplocalAoA_dpiAoA)
self.__compute_dpgamma_dpiAoA()
self.__compute_dpiAoAnew_dpiAoA()
self.__dpR_dpiAoA=numpy.diag(ones([N]))-self.__dpiAoAnew_dpiAoA
return self.__dpR_dpiAoA
def comp_dpR_dpchi(self):
self.__compute_dplocalAoA_dpchi()
self.__compute_dpgamma_dpchi()
self.__compute_dpiAoAnew_dpchi()
self.__dpR_dpchi = -self.__dpiAoAnew_dpchi
return self.__dpR_dpchi
def comp_dpR_dpthetaY(self):
K=self.get_K()
self.__compute_dpgamma_dpthetaY()
self.__dpR_dpthetaY = -dot(K,self.__dpgamma_dpthetaY)
return self.__dpR_dpthetaY
def comp_dpR_dpAoA(self):
K=self.get_K()
self.__compute_dpgamma_dpAoA()
self.__dpR_dpAoA = -dot(K,self.__dpgamma_dpAoA)
return self.__dpR_dpAoA
def __compute_dpgamma_dpAoA(self):
N=self.get_N()
Mach = self.get_OC().get_Mach()
for i in xrange(N):
self.__dpgamma_dplocalAoA[i,i] = self.get_airfoils()[i].dpgamma_dpAoA(self.__localAoA[i],Mach)
self.__dpgamma_dpAoA = dot(self.__dpgamma_dplocalAoA,self.__dplocalAoA_dpAoA)
def __compute_dpgamma_dpthetaY(self):
N=self.get_N()
Mach = self.get_OC().get_Mach()
for i in xrange(N):
self.__dpgamma_dplocalAoA[i,i] = self.get_airfoils()[i].dpgamma_dpAoA(self.__localAoA[i],Mach)
self.__dpgamma_dpthetaY = dot(self.__dpgamma_dplocalAoA,self.__dplocalAoA_dpthetaY)
def __compute_dplocalAoA_dpchi(self):
N=self.get_N()
twist_grad = self.get_wing_param().get_twist_grad()
AoA_grad = self.get_wing_param().get_AoA_grad()
if AoA_grad is None:
for i in xrange(N):
self.__dplocalAoA_dpchi[i,:] =twist_grad[i,:] # + dAoAdksi ??
else:
for i in xrange(N):
self.__dplocalAoA_dpchi[i,:] = AoA_grad[:] + twist_grad[i,:]
def __compute_dpgamma_dpchi(self):
N=self.get_N()
Mach = self.get_OC().get_Mach()
for i in xrange(N):
self.__dpgamma_dpchi[i,:] = self.get_airfoils()[i].dpgamma_dpchi(self.__localAoA[i],Mach)
self.__dpgamma_dpchi = self.__dpgamma_dpchi + dot(self.__dpgamma_dplocalAoA,self.__dplocalAoA_dpchi)
def __compute_dpiAoAnew_dpchi(self):
K=self.get_K()
dK_dchi=self.get_dK_dchi()
ndv=self.get_ndv()
self.__dpiAoAnew_dpchi = dot(K,self.__dpgamma_dpchi)
for n in xrange(ndv):
self.__dpiAoAnew_dpchi[:,n] += dot(dK_dchi[:,:,n],self.__gamma)
def __compute_localAoA(self):
N=self.get_N()
Thetay = self.get_wing_param().get_thetaY()
twist = self.get_wing_param().get_twist()
AoA = self.get_wing_param().get_AoA()
if AoA is None:
AoA = self.get_OC().get_AoA_rad()
else:
self.get_OC().set_AoA(AoA*180./numpy.pi)
# Why this formula ? twist increases the local airfoil angle of attack normally...
#self.__localAoA=alpha-iaOa-self.get_wing_geom().get_twist()
self.__localAoA = AoA + twist + self.__iAoA + Thetay
for i in xrange(N):
if self.__localAoA[i] > numpy.pi/2. or self.__localAoA[i] < -numpy.pi/2.:
raise Exception, "Local angle of attack out of bounds [-pi/2, pi/2]"
def __compute_gamma(self):
"""
Update the circulation
"""
N=self.get_N()
Mach = self.get_OC().get_Mach()
for i in xrange(N):
self.__gamma[i] = self.get_airfoils()[i].gamma(self.__localAoA[i],Mach)
def __compute_dpgamma_dpiAoA(self):
N=self.get_N()
Mach = self.get_OC().get_Mach()
for i in xrange(N):
self.__dpgamma_dplocalAoA[i,i] = self.get_airfoils()[i].dpgamma_dpAoA(self.__localAoA[i],Mach)
self.__dpgamma_dpiAoA = dot(self.__dpgamma_dplocalAoA,self.__dplocalAoA_dpiAoA)
def __compute_iAoAnew(self):
'''
Computes the induced angle on an airfoil for a given circulation on the wing.
'''
K=self.get_K()
self.__iAoANew = dot(K,self.__gamma)
def __compute_dpiAoAnew_dpiAoA(self):
"""
Computes the derivative dpiAoAnew_dpiAoA
"""
K=self.get_K()
self.__dpiAoAnew_dpiAoA = dot(K,self.__dpgamma_dpiAoA)
def write_gamma_to_file(self):
'''
Writes the circulation repartition in a file
'''
y = self.get_wing_param().get_XYZ()[1,:]
if self.__gamma_f_name is None:
gamma_f_name='gamma.dat'
else:
gamma_f_name=self.__gamma_f_name
mod_gamma_f_name=self.get_tag()+'_'+gamma_f_name
fid=open(mod_gamma_f_name,'w')
line="#Slice\t%24s"%"y"+"\t%24s"%"Circulation"+"\n"
fid.write(line)
i=0
for i in range(len(self.__gamma)):
line=str(i)+"\t%24.16e"%y[i]+"\t%24.16e"%self.__gamma[i]+"\n"
fid.write(line)
fid.close()
fid=open(self.get_tag()+'_iAoA.dat','w')
line="#Slice\t%24s"%"y"+"\t%24s"%"iAoA"+"\t%24s"%"iAoA_deg"+"\n"
fid.write(line)
i=0
for i in range(len(self.__gamma)):
line=str(i)+"\t%24.16e"%y[i]+"\t%24.16e"%self.__iAoA[i]+"\t%24.16e"%(self.__iAoA[i]*self.RAD_TO_DEG)+"\n"
fid.write(line)
fid.close()
OC.compute_atmosphere()
wing_param=Wing_Broken('broken_wing',n_sect=20)
wing_param.import_BC_from_file('input_parameters.par')
wing_param.build_linear_airfoil(OC, AoA0=0.0, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
wing_param.plot()
N = wing_param.get_n_sect()
iAoA0=numpy.zeros(N)
DLLM = DLLMSolver('test',wing_param,OC)
NRPb = NewtonRaphsonProblem(iAoA0, DLLM.comp_R, DLLM.comp_dpR_dpiAoA)
NRPb.set_relax_factor(0.99)
NRPb.set_stop_residual(1.e-9)
NRPb.set_max_iterations(100)
iAoA=NRPb.solve()
DLLM.set_direct_computed()
print iAoA
DLLM.comp_dpR_dpchi()
dpRdpthetaY=DLLM.comp_dpR_dpthetaY()
print 'dpRdpthetaY=',dpRdpthetaY
print DLLM.get_iAoA()
class DLLMDirect:
"""
Direct solver for the lifting line wing model
"""
DEG_TO_RAD = np.pi / 180.
RAD_TO_DEG = 180. / np.pi
def __init__(self, LLW, verbose = 0):
self.__LLW = LLW
self.__verbose = verbose
self.__computed = False
self.__gamma_f_name = None
# initialize local variables
self.__init_local_variables()
# initialize the Newton-Raphson problem
self.__NRPb = None
self.__init_Newton_Raphson()
#-- Accessors
def get_tag(self):
return self.__LLW.get_tag()
def get_grad_active(self):
return self.__LLW.get_grad_active()
def get_geom(self):
return self.__LLW.get_geom()
def get_airfoils(self):
return self.__LLW.get_airfoils()
def get_K(self):
return self.__LLW.get_K()
def get_dK_dchi(self):
return self.__LLW.get_dK_dchi()
def get_N(self):
return self.get_geom().get_n_sect()
def get_ndv(self):
return self.get_geom().get_ndv()
def get_OC(self):
return self.__LLW.get_OC()
def get_iAoA(self):
return self.__iAoA
def get_localAoA(self):
return self.__localAoA
def get_R(self):
return self.__R
def get_dpR_dpiAoA(self):
return self.__dpR_dpiAoA
def get_dpR_dpchi(self):
return self.__dpR_dpchi
def get_dplocalAoA_dpiAoA(self):
return self.__dplocalAoA_dpiAoA
def get_dplocalAoA_dpAoA(self):
return self.__dplocalAoA_dpAoA
def get_dplocalAoA_dpchi(self):
return self.__dplocalAoA_dpchi
def get_dplocalAoA_dpthetaY(self):
return self.__dplocalAoA_dpthetaY
def get_convergence_history(self):
"""
Accessor to the last computation convergence history as a list of residuals normalized by the first iteration residual.
"""
return self.__residuals_hist
def is_computed(self):
return self.__computed
#-- Setters
def set_computed(self, bool=True):
self.__computed = bool
def set_gamma_file_name(self, gamma_f_name):
self.__gamma_f_name = gamma_f_name
#-- Newton-Raphson related methods
def __init_Newton_Raphson(self):
N = self.get_N()
iAoA0 = zeros(N)
self.comp_R(iAoA0)
self.comp_dpR_dpiAoA(iAoA0)
self.__NRPb = NewtonRaphsonProblem(iAoA0,self.comp_R,self.comp_dpR_dpiAoA,verbose = self.__verbose)
self.__NRPb.set_relax_factor(0.99)
self.__NRPb.set_stop_residual(1.e-9)
self.__NRPb.set_max_iterations(100)
def set_relax_factor(self, relax_factor):
self.__NRPb.set_relax_factor(relax_factor)
def set_stop_residual(self, residual):
self.__NRPb.set_stop_residual(residual)
def set_max_iterations(self, max_it):
self.__NRPb.set_max_iterations(max_it)
def set_method(self, method):
self.__NRPb.set_method(method)
#-- Computation related methods
def run(self):
grad_active = self.get_grad_active()
self.__NRPb.solve()
self.set_computed(True)
self.write_gamma_to_file()
if grad_active:
self.comp_dpR_dpchi()
def __init_local_variables(self):
# Initializing local variables for lifting line computations
# Residual variables
N = self.get_N()
ndv = self.get_ndv()
grad_active = self.get_grad_active()
self.__R = zeros([N])
self.__dpR_dpiAoA = None
self.__dpR_dpchi = None
self.__dpR_dpthetaY = None
self.__dpR_dpAoA = None
# Angle of attack variables
self.__localAoA = zeros([N])
self.__dplocalAoA_dpiAoA = diag(ones([N])) # This is a constant matrix
self.__dplocalAoA_dpthetaY = diag(ones([N])) # This is a constant matrix
self.__dplocalAoA_dpAoA = ones(N)
if grad_active:
self.__dplocalAoA_dpchi = zeros([N, ndv])
else:
self.__dplocalAoA_dpchi = None
# Induced angle of attack variables
self.__iAoA = None
self.__iAoANew = None
if grad_active:
self.__dpiAoAnew_dpchi = zeros([N, ndv])
else:
self.__dpiAoAnew_dpchi = None
self.__dpiAoAnew_dpiAoA = None
# Circulation variables
self.__gamma = zeros(N)
self.__dpgamma_dpiAoA = None
self.__dpgamma_dpthetaY = None
self.__dpgamma_dpAoA = None
self.__dpgamma_dplocalAoA = zeros([N, N])
if grad_active:
self.__dpgamma_dpchi = zeros([N, ndv])
else:
self.__dpgamma_dpchi = None
#-- Residual related methods
def comp_R(self, iAoA):
self.__iAoA = iAoA
self.__compute_localAoA()
self.__compute_gamma()
self.__compute_iAoAnew()
self.__R = self.__iAoA - self.__iAoANew
return self.__R
def comp_dpR_dpiAoA(self, iAoA):
N = self.get_N()
# R = self.comp_R(iAoA)
# dplocalAoA_dpiAoA is a constant matrix, no need to compute it
# (self.__dplocalAoA_dpiAoA)
self.__compute_dpgamma_dpiAoA()
self.__compute_dpiAoAnew_dpiAoA()
self.__dpR_dpiAoA = np.diag(ones([N])) - self.__dpiAoAnew_dpiAoA
return self.__dpR_dpiAoA
def comp_dpR_dpchi(self):
self.__compute_dplocalAoA_dpchi()
self.__compute_dpgamma_dpchi()
self.__compute_dpiAoAnew_dpchi()
self.__dpR_dpchi = -self.__dpiAoAnew_dpchi
return self.__dpR_dpchi
def comp_dpR_dpthetaY(self):
K = self.get_K()
self.__compute_dpgamma_dpthetaY()
self.__dpR_dpthetaY = -dot(K, self.__dpgamma_dpthetaY)
return self.__dpR_dpthetaY
def comp_dpR_dpAoA(self):
K = self.get_K()
self.__compute_dpgamma_dpAoA()
self.__dpR_dpAoA = -dot(K, self.__dpgamma_dpAoA)
return self.__dpR_dpAoA
def __compute_dpgamma_dpAoA(self):
N = self.get_N()
for i in xrange(N):
self.__dpgamma_dplocalAoA[i,i] = self.get_airfoils()[i].dgamma_dAoA
self.__dpgamma_dpAoA = dot(self.__dpgamma_dplocalAoA,self.__dplocalAoA_dpAoA)
def __compute_dpgamma_dpthetaY(self):
N = self.get_N()
for i in xrange(N):
self.__dpgamma_dplocalAoA[i,i] = self.get_airfoils()[i].dgamma_dAoA
self.__dpgamma_dpthetaY = dot(self.__dpgamma_dplocalAoA,self.__dplocalAoA_dpthetaY)
def __compute_dplocalAoA_dpchi(self):
N = self.get_N()
twist_grad = self.get_geom().get_twist_grad()
AoA_grad = self.get_geom().get_AoA_grad()
if AoA_grad is None:
self.__dplocalAoA_dpchi = twist_grad
else:
for i in xrange(N):
self.__dplocalAoA_dpchi[i, :] = AoA_grad[:] + twist_grad[i, :]
def __compute_dpgamma_dpchi(self):
N = self.get_N()
for i in xrange(N):
self.__dpgamma_dpchi[i,:] = self.get_airfoils()[i].dgamma_dchi
self.__dpgamma_dpchi = self.__dpgamma_dpchi + dot(self.__dpgamma_dplocalAoA, self.__dplocalAoA_dpchi)
def __compute_dpiAoAnew_dpchi(self):
K = self.get_K()
dK_dchi = self.get_dK_dchi()
ndv = self.get_ndv()
self.__dpiAoAnew_dpchi = dot(K, self.__dpgamma_dpchi)
for n in xrange(ndv):
self.__dpiAoAnew_dpchi[:, n] += dot(dK_dchi[:, :, n], self.__gamma)
def __compute_localAoA(self):
N = self.get_N()
Thetay = self.get_geom().get_thetaY()
twist = self.get_geom().get_twist()
AoA = self.get_geom().get_AoA()
if AoA is None:
AoA = self.get_OC().get_AoA_rad()
else:
self.get_OC().set_AoA(AoA * 180. / np.pi)
# Why this formula ? twist increases the local airfoil angle of attack normally...
# self.__localAoA=alpha-iaOa-self.get_wing_geom().get_twist()
self.__localAoA = AoA + twist + self.__iAoA + Thetay
for i in xrange(N):
if self.__localAoA[i] > np.pi / 2. or self.__localAoA[i] < -np.pi / 2.:
raise Exception("Local angle of attack out of bounds [-pi/2, pi/2]")
def __compute_gamma(self):
"""
Update the circulation
"""
N = self.get_N()
Mach = self.get_OC().get_Mach()
for i in xrange(N):
self.get_airfoils()[i].compute(self.__localAoA[i],Mach)
self.__gamma[i] = self.get_airfoils()[i].gamma
if np.isnan(self.get_airfoils()[i].gamma):
af = self.get_airfoils()[i]
print 'Lref = ',af.get_Lref()
print 'Sref = ',af.get_Sref()
print 'Cl = ',af.Cl
def __compute_dpgamma_dpiAoA(self):
N = self.get_N()
for i in xrange(N):
self.__dpgamma_dplocalAoA[i,i] = self.get_airfoils()[i].dgamma_dAoA
self.__dpgamma_dpiAoA = dot(self.__dpgamma_dplocalAoA, self.__dplocalAoA_dpiAoA)
def __compute_iAoAnew(self):
'''
Computes the induced angle on an airfoil for a given circulation on the wing.
'''
K = self.get_K()
self.__iAoANew = dot(K, self.__gamma)
def __compute_dpiAoAnew_dpiAoA(self):
"""
Computes the derivative dpiAoAnew_dpiAoA
"""
K = self.get_K()
self.__dpiAoAnew_dpiAoA = dot(K, self.__dpgamma_dpiAoA)
def write_gamma_to_file(self):
'''
Writes the circulation repartition in a file
'''
y = self.get_geom().get_XYZ()[1, :]
if self.__gamma_f_name is None:
gamma_f_name = 'gamma.dat'
else:
gamma_f_name = self.__gamma_f_name
mod_gamma_f_name = self.get_tag() + '_' + gamma_f_name
fid = open(mod_gamma_f_name, 'w')
line = "#Slice\t%24s" % "y" + "\t%24s" % "Circulation" + "\n"
fid.write(line)
i = 0
for i in range(len(self.__gamma)):
line = str(i) + "\t%24.16e" % y[i] + \
"\t%24.16e" % self.__gamma[i] + "\n"
fid.write(line)
fid.close()
fid = open(self.get_tag() + '_iAoA.dat', 'w')
line = "#Slice\t%24s" % "y" + "\t%24s" % "iAoA" + \
"\t%24s" % "iAoA_deg" + "\n"
fid.write(line)
i = 0
for i in range(len(self.__gamma)):
line = str(i) + "\t%24.16e" % y[i] + "\t%24.16e" % self.__iAoA[
i] + "\t%24.16e" % (self.__iAoA[i] * self.RAD_TO_DEG) + "\n"
fid.write(line)
fid.close()
def plot(self):
name = self.get_tag()
Y_list = self.get_geom().get_XYZ()[1,:]
plt.xlim(1.1*Y_list[0], 1.1*Y_list[-1])
plt.xlabel('y')
plt.ylabel('gamma')
plt.plot(Y_list,self.__gamma)
plt.rc("font", size=14)
plt.savefig(name+"_gamma_distrib.png",format='png')
plt.close()
plt.xlim(1.1*Y_list[0], 1.1*Y_list[-1])
plt.xlabel('y')
plt.ylabel('iAoA')
plt.plot(Y_list,self.__iAoA*self.RAD_TO_DEG)
plt.rc("font", size=14)
plt.savefig(name+"_iAoA_distrib.png",format='png')
plt.close()
class DLLMTargetLift(DLLMSolver):
ERROR_MSG='ERROR in DLLMTargetLift.'
def __init__(self, tag, geom, OC,verbose = 0, grad_active=True):
self.__verbose = verbose
DLLMSolver.__init__(self, tag, geom, OC, verbose = self.__verbose, grad_active=grad_active)
self.__N = self.get_geom().get_n_sect()
self.__ndv = self.get_geom().get_ndv()
self.__R_TL = numpy.zeros(self.__N+1)
self.__dpR_TL_dpW = numpy.zeros((self.__N+1,self.__N+1))
self.__dpR_TL_dpchi = numpy.zeros((self.__N+1,self.__ndv))
self.__dpF_list_dpW = None
self.__target_Lift = 0.
# initialize the Newton-Raphson problem
self.__NRPb = None
self.__init_Newton_Raphson()
# -- Accessors
def get_target_Lift(self):
return self.__target_Lift
def set_target_Lift(self, target):
self.__target_Lift = target
#-- Newton-Raphson related methods
def __init_Newton_Raphson(self):
W0= numpy.zeros(self.__N+1)
self.__NRPb = NewtonRaphsonProblem(W0, self.comp_R_TL, self.comp_dpR_TL_dpW, verbose = self.__verbose)
self.__NRPb.set_relax_factor(0.99)
self.__NRPb.set_stop_residual(1.e-9)
self.__NRPb.set_max_iterations(100)
def set_relax_factor(self, relax_factor):
self.__NRPb.set_relax_factor(relax_factor)
def set_stop_residual(self, residual):
self.__NRPb.set_stop_residual(residual)
def set_max_iterations(self, max_it):
self.__NRPb.set_max_iterations(max_it)
def set_method(self, method):
self.__NRPb.set_method(method)
#-- Residual Related method
def comp_R_TL(self, W):
DLLMDirect = self.get_DLLMDirect()
DLLMPost = self.get_DLLMPost()
OC = self.get_OC()
iAoA = W[0:self.__N]
AoA = W[self.__N]
OC.set_AoA_rad(AoA)
R = DLLMDirect.comp_R(iAoA)
DLLMPost.run(F_list_names=['Lift'])
self.__R_TL[:self.__N] = R[:]
self.__R_TL[self.__N] = DLLMPost.Lift- self.__target_Lift
return self.__R_TL
def comp_dpR_TL_dpW(self, W):
DLLMDirect = self.get_DLLMDirect()
DLLMPost = self.get_DLLMPost()
OC = self.get_OC()
iAoA = W[0:self.__N]
AoA = W[self.__N]
OC.set_AoA_rad(AoA)
# Init information
DLLMDirect.comp_R(iAoA)
dpR_dpiAoA = DLLMDirect.comp_dpR_dpiAoA(iAoA)
dpR_dpAoA = DLLMDirect.comp_dpR_dpAoA()
DLLMPost.run(F_list_names=['Lift'])
dpLift_dpiAoA = DLLMPost.dpLift_dpiAoA
dpLift_dpAoA = DLLMPost.dpLift_dpAoA
self.__dpR_TL_dpW[0:self.__N,0:self.__N] = dpR_dpiAoA[:,:]
self.__dpR_TL_dpW[self.__N,0:self.__N] = dpLift_dpiAoA[:]
self.__dpR_TL_dpW[0:self.__N,self.__N] = dpR_dpAoA[:]
self.__dpR_TL_dpW[self.__N,self.__N] = dpLift_dpAoA
return self.__dpR_TL_dpW
def get_R(self):
return self.__R_TL
def get_dpR_dpW(self):
return self.__dpR_TL_dpW
def get_dpR_dpchi(self):
DLLMDirect = self.get_DLLMDirect()
DLLMPost = self.get_DLLMPost()
dpR_dpchi = DLLMDirect.get_dpR_dpchi()
dpLift_dpchi = DLLMPost.dpLift_dpchi
self.__dpR_TL_dpchi[:self.__N,:] = dpR_dpchi[:,:]
self.__dpR_TL_dpchi[self.__N,:] = dpLift_dpchi[:]
return self.__dpR_TL_dpchi
def get_dpF_list_dpW(self):
DLLMPost = self.get_DLLMPost()
dpF_list_dpiAoA = DLLMPost.get_dpF_list_dpiAoA()
dpF_list_dpAoA = DLLMPost.get_dpF_list_dpAoA()
dim = len(dpF_list_dpiAoA)
self.__dpF_list_dpW = numpy.zeros((dim,self.__N+1))
for i in xrange(dim):
self.__dpF_list_dpW[i,:self.__N] = dpF_list_dpiAoA[i,:]
self.__dpF_list_dpW[i,self.__N] = dpF_list_dpAoA[i]
return self.__dpF_list_dpW
def run_direct(self):
DLLMDirect = self.get_DLLMDirect()
# W0= numpy.zeros(self.__N+1)
# self.__NRPb.valid_jacobian(W0, iprint=True)
self.__NRPb.solve()
DLLMDirect.set_computed(True)
DLLMDirect.write_gamma_to_file()
if self.get_grad_active():
DLLMDirect.comp_dpR_dpchi()
