def test_Wing_param_build_wing(self):
wing_param = Wing_param('test_param', geom_type='Broken', n_sect=20)
try:
wing_param.build_wing()
ok = True
except:
ok = False
assert (ok)
def test_Wing_param_build_wing(self):
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
try:
wing_param.build_wing()
ok=True
except:
ok=False
assert(ok)
def __config_param(self):
input_keys=self.__config_dict.keys()
geom_type_key=self.__tag+'.param.geom_type'
if geom_type_key in input_keys:
geom_type = self.__config_dict[geom_type_key]
else:
geom_type= 'Broken'
n_sect_key=self.__tag+'.param.n_sect'
if n_sect_key in input_keys:
n_sect = self.__config_dict[n_sect_key]
else:
n_sect = 20
self.__wing_param = Wing_param(self.__tag+'.param',geom_type=geom_type,n_sect=n_sect)
self.__wing_param.set_AoA_id(self.__AoA_id)
self.__wing_param.config_from_dict(self.__OC, self.__config_dict)
def __set_wing_param_values(self, wing_param_name='test_param'):
"""Method for wing parameters variables setting
@param wing_param_name : wing parametrization names
"""
self.__wing_param = Wing_param(wing_param_name,
geom_type='Broken', n_sect=self.N * 2)
self.__wing_param.build_wing()
for i in xrange(self.N):
self.__wing_param.set_value('rtwist%s' % i, 0.)
for param in Wing_param.DISCRETE_ATTRIBUTES_LIST:
self.__wing_param.set_value(param, getattr(self, param))
def __config_param(self):
input_keys=self.__config_dict.keys()
geom_type_key=self.__tag+'.param.geom_type'
if geom_type_key in input_keys:
geom_type = self.__config_dict[geom_type_key]
else:
geom_type= 'Broken'
n_sect_key=self.__tag+'.param.n_sect'
if n_sect_key in input_keys:
n_sect = self.__config_dict[n_sect_key]
else:
n_sect = 20
self.__wing_param = Wing_param(self.__tag+'.param',geom_type=geom_type,n_sect=n_sect)
self.__wing_param.set_AoA_id(self.__AoA_id)
self.__wing_param.config_from_dict(self.__OC, self.__config_dict)
class DLLMWrapper():
ERROR_MSG = 'ERROR in DLLMWrapper.'
WARNING_MSG = 'WARNING in DLLMWrapper.'
POS_SOLVER = ['Solver','TargetCl','TargetLift']
POS_FMT = ['list','numpy']
def __init__(self, tag):
"""
Wrapper for the DLLM solver
"""
self.__tag = tag
self.__OC = None # Operating condition
self.__wing_param = None # Wing_param class
self.__DLLM_solver = None # DLLM Solver class
self.__config_dict = None
self.__out_format = 'list'
self.__grad_format = 'list'
self.__AoA_id = 'AoA'
self.__F_list = None
self.__F_list_grad = None
#-- Accessors
def get_OC(self):
return self.__OC
def get_wing_param(self):
return self.__wing_param
def get_DLLM_solver(self):
return self.__DLLM_solver
def get_tags_x0_and_bounds(self):
tags=self.__wing_param.get_dv_id_list()
x0=self.__wing_param.get_dv_array()
bounds=self.__wing_param.get_bounds_array()
return tags,x0,bounds
def get_x0_and_bounds(self):
x0=self.__wing_param.get_dv_array()
bounds=self.__wing_param.get_bounds_array()
return x0,bounds
def get_x0(self):
return self.get_x()
def get_x(self):
x=self.__wing_param.get_dv_array()
return x
def get_F_list_names(self):
return self.__DLLM_solver.get_F_list_names()
def get_F_list(self):
return self.__F_list
def get_F_list_grad(self):
return self.__F_list_grad
def get_F_list_and_grad(self):
return self.__F_list, self.__F_list_grad
#-- Setters
def set_AoA_id(self, AoA_id):
self.__AoA_id = AoA_id
def set_out_format(self, format):
WARNING_MSG=self.WARNING_MSG+'set_out_format: '
if format not in self.POS_FMT:
print WARNING_MSG+'format = '+str(format)+' not in '+str(self.POS_FMT)+'. Set to default out format = list'
format='list'
self.__out_format = format
def set_grad_format(self, format):
WARNING_MSG=self.WARNING_MSG+'set_grad_format: '
if format not in self.POS_FMT:
print WARNING_MSG+'format = '+str(format)+' not in '+str(self.POS_FMT)+'. Set to default grad format = list'
format='list'
self.__grad_format = format
#-- Public methods
def configure(self, config_dict):
self.__config_dict = config_dict
self.__config_OC()
self.__config_param()
self.__config_DLLM()
def run(self, x):
self.__wing_param.update_from_x_list(x)
self.__DLLM_solver.set_wing_param(self.__wing_param)
F_list=self.analysis()
return F_list
def run_grad(self, x):
self.__wing_param.update_from_x_list(x)
self.__DLLM_solver.set_wing_param(self.__wing_param)
F_list_grad=self.analysis_grad()
return F_list_grad
def run_and_grad(self, x):
self.__wing_param.update_from_x_list(x)
self.__DLLM_solver.set_wing_param(self.__wing_param)
F_list,F_list_grad = self.analysis_and_grad()
return F_list,F_list_grad
def analysis(self):
print self.__wing_param
self.__DLLM_solver.run_direct()
self.__DLLM_solver.run_post()
F_list = self.__DLLM_solver.get_F_list()
if self.__out_format == 'list':
F_list=F_list.tolist()
self.__F_list = F_list
return F_list
def analysis_grad(self):
print self.__wing_param
self.__DLLM_solver.run_direct()
self.__DLLM_solver.run_post()
self.__DLLM_solver.run_adjoint()
F_list_grad=self.__DLLM_solver.get_dF_list_dchi()
if self.__grad_format == 'numpy':
F_list_grad=numpy.array(F_list_grad)
self.__F_list_grad = F_list_grad
return F_list_grad
def analysis_and_grad(self):
print self.__wing_param
self.__DLLM_solver.run_direct()
self.__DLLM_solver.run_post()
self.__DLLM_solver.run_adjoint()
F_list = self.__DLLM_solver.get_F_list()
F_list_grad=self.__DLLM_solver.get_dF_list_dchi()
if self.__out_format == 'list':
F_list=F_list.tolist()
if self.__grad_format == 'numpy':
F_list_grad=numpy.array(F_list_grad)
self.__F_list = F_list
self.__F_list_grad = F_list_grad
return F_list,F_list_grad
def export_results(self):
fid=open(self.__tag+'.res.dat','w')
res=[self.__F_list,self.__F_list_grad]
cPickle.dump(res, fid)
fid.close()
def import_results(self):
fid=open(self.__tag+'.res.dat','r')
res=cPickle.load(fid)
fid.close()
self.__F_list=res[0]
self.__F_list_grad=res[1]
#-- Private methods
def __config_OC(self):
self.__OC = OperatingCondition(self.__tag+'.OC')
self.__OC.config_from_dict(self.__config_dict)
def __config_param(self):
input_keys=self.__config_dict.keys()
geom_type_key=self.__tag+'.param.geom_type'
if geom_type_key in input_keys:
geom_type = self.__config_dict[geom_type_key]
else:
geom_type= 'Broken'
n_sect_key=self.__tag+'.param.n_sect'
if n_sect_key in input_keys:
n_sect = self.__config_dict[n_sect_key]
else:
n_sect = 20
self.__wing_param = Wing_param(self.__tag+'.param',geom_type=geom_type,n_sect=n_sect)
self.__wing_param.set_AoA_id(self.__AoA_id)
self.__wing_param.config_from_dict(self.__OC, self.__config_dict)
def __config_DLLM(self):
WARNING_MSG=self.WARNING_MSG+'__config_DLLM: '
input_keys=self.__config_dict.keys()
type_key = self.__tag+'.DLLM.type'
type = self.__config_dict[type_key]
if type not in self.POS_SOLVER:
print WARNING_MSG+'solver_type = '+str(solve_type)+' not in '+str(self.POS_SOLVER)+'. Set to default solver_type = Solver'
type='Solver'
if type == 'Solver':
self.__DLLM_solver = DLLMSolver(self.__tag,self.__wing_param,self.__OC)
elif type == 'TargetCl':
self.__DLLM_solver = DLLMTargetCl(self.__tag,self.__wing_param,self.__OC)
target_Cl_key = self.__tag+'.DLLM.target_Cl'
target_Cl = self.__config_dict[target_Cl_key]
self.__DLLM_solver.set_target_Cl(target_Cl)
elif type == 'TargetLift':
self.__DLLM_solver = DLLMTargetLift(self.__tag,self.__wing_param,self.__OC)
target_Lift_key = self.__tag+'.DLLM.target_Lift'
target_Lift = self.__config_dict[target_Lift_key]
self.__DLLM_solver.set_target_Lift(target_Lift)
method_key = self.__tag+'.DLLM.method'
if method_key in input_keys:
method = self.__config_dict[method_key]
self.__DLLM_solver.set_method(method)
relax_factor_key = self.__tag+'.DLLM.relax_factor'
if relax_factor_key in input_keys:
relax_factor = self.__config_dict[relax_factor_key]
self.__DLLM_solver.set_relax_factor(relax_factor)
stop_residual_key = self.__tag+'.DLLM.stop_residual'
if stop_residual_key in input_keys:
stop_residual = self.__config_dict[stop_residual_key]
self.__DLLM_solver.set_stop_residual(stop_residual)
max_iterations_key = self.__tag+'.DLLM.max_iterations'
if max_iterations_key in input_keys:
max_iterations = self.__config_dict[max_iterations_key]
self.__DLLM_solver.set_max_iterations(max_iterations)
gamma_file_name_key = self.__tag+'.DLLM.gamma_file_name'
if gamma_file_name_key in input_keys:
gamma_file_name = self.__config_dict[gamma_file_name_key]
self.__DLLM_solver.set_gamma_file_name(gamma_file_name)
F_list_names_key = self.__tag+'.DLLM.F_list_names'
if F_list_names_key in input_keys:
F_list_names = self.__config_dict[F_list_names_key]
self.__DLLM_solver.set_F_list_names(F_list_names)
from DLLM.DLLMGeom.wing_param import Wing_param
from DLLM.DLLMKernel.DLLMTargetCl import DLLMTargetCl
from MDOTools.OC.operating_condition import OperatingCondition
import numpy
import sys
OC=OperatingCondition('cond1')
OC.set_Mach(0.8)
OC.set_AoA(3.5)
OC.set_altitude(10000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',34.1)
wing_param.set_value('sweep',34.)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',6.1)
wing_param.set_value('break_chord',4.6)
wing_param.set_value('tip_chord',1.5)
wing_param.set_value('root_height',1.28)
wing_param.set_value('break_height',0.97)
wing_param.set_value('tip_height',0.33)
wing_param.convert_to_design_variable('span',(10.,50.))
wing_param.convert_to_design_variable('sweep',(0.,40.))
wing_param.convert_to_design_variable('break_percent',(20.,40.))
wing_param.convert_to_design_variable('root_chord',(5.,7.))
wing_param.convert_to_design_variable('break_chord',(3.,5.))
class DLLMWrapper():
ERROR_MSG = 'ERROR in DLLMWrapper.'
WARNING_MSG = 'WARNING in DLLMWrapper.'
POS_SOLVER = ['Solver','TargetCl','TargetLift']
POS_FMT = ['list','numpy']
def __init__(self, tag):
"""
Wrapper for the DLLM solver
"""
self.__tag = tag
self.__OC = None # Operating condition
self.__wing_param = None # Wing_param class
self.__DLLM_solver = None # DLLM Solver class
self.__config_dict = None
self.__out_format = 'list'
self.__grad_format = 'list'
self.__AoA_id = 'AoA'
self.__F_list = None
self.__F_list_grad = None
#-- Accessors
def get_OC(self):
return self.__OC
def get_wing_param(self):
return self.__wing_param
def get_DLLM_solver(self):
return self.__DLLM_solver
def get_tags_x0_and_bounds(self):
tags=self.__wing_param.get_dv_id_list()
x0=self.__wing_param.get_dv_array()
bounds=self.__wing_param.get_bounds_array()
return tags,x0,bounds
def get_x0_and_bounds(self):
x0=self.__wing_param.get_dv_array()
bounds=self.__wing_param.get_bounds_array()
return x0,bounds
def get_x0(self):
return self.get_x()
def get_x(self):
x=self.__wing_param.get_dv_array()
return x
def get_F_list_names(self):
return self.__DLLM_solver.get_F_list_names()
def get_F_list(self):
return self.__F_list
def get_F_list_grad(self):
return self.__F_list_grad
def get_F_list_and_grad(self):
return self.__F_list, self.__F_list_grad
#-- Setters
def set_AoA_id(self, AoA_id):
self.__AoA_id = AoA_id
def set_out_format(self, format):
WARNING_MSG=self.WARNING_MSG+'set_out_format: '
if format not in self.POS_FMT:
print WARNING_MSG+'format = '+str(format)+' not in '+str(self.POS_FMT)+'. Set to default out format = list'
format='list'
self.__out_format = format
def set_grad_format(self, format):
WARNING_MSG=self.WARNING_MSG+'set_grad_format: '
if format not in self.POS_FMT:
print WARNING_MSG+'format = '+str(format)+' not in '+str(self.POS_FMT)+'. Set to default grad format = list'
format='list'
self.__grad_format = format
#-- Public methods
def configure(self, config_dict):
self.__config_dict = config_dict
self.__config_OC()
self.__config_param()
self.__config_DLLM()
def run(self, x):
self.__wing_param.update_from_x_list(x)
self.__DLLM_solver.set_wing_param(self.__wing_param)
F_list=self.analysis()
return F_list
def run_grad(self, x):
self.__wing_param.update_from_x_list(x)
self.__DLLM_solver.set_wing_param(self.__wing_param)
F_list_grad=self.analysis_grad()
return F_list_grad
def run_and_grad(self, x):
self.__wing_param.update_from_x_list(x)
self.__DLLM_solver.set_wing_param(self.__wing_param)
F_list,F_list_grad = self.analysis_and_grad()
return F_list,F_list_grad
def analysis(self):
print self.__wing_param
self.__DLLM_solver.run_direct()
self.__DLLM_solver.run_post()
F_list = self.__DLLM_solver.get_F_list()
if self.__out_format == 'list':
F_list=F_list.tolist()
self.__F_list = F_list
return F_list
def analysis_grad(self):
print self.__wing_param
self.__DLLM_solver.run_direct()
self.__DLLM_solver.run_post()
self.__DLLM_solver.run_adjoint()
F_list_grad=self.__DLLM_solver.get_dF_list_dchi()
if self.__grad_format == 'numpy':
F_list_grad=numpy.array(F_list_grad)
self.__F_list_grad = F_list_grad
return F_list_grad
def analysis_and_grad(self):
print self.__wing_param
self.__DLLM_solver.run_direct()
self.__DLLM_solver.run_post()
self.__DLLM_solver.run_adjoint()
F_list = self.__DLLM_solver.get_F_list()
F_list_grad=self.__DLLM_solver.get_dF_list_dchi()
if self.__out_format == 'list':
F_list=F_list.tolist()
if self.__grad_format == 'numpy':
F_list_grad=numpy.array(F_list_grad)
self.__F_list = F_list
self.__F_list_grad = F_list_grad
return F_list,F_list_grad
def export_results(self):
fid=open(self.__tag+'.res.dat','w')
res=[self.__F_list,self.__F_list_grad]
cPickle.dump(res, fid)
fid.close()
def import_results(self):
fid=open(self.__tag+'.res.dat','r')
res=cPickle.load(fid)
fid.close()
self.__F_list=res[0]
self.__F_list_grad=res[1]
#-- Private methods
def __config_OC(self):
self.__OC = OperatingCondition(self.__tag+'.OC')
self.__OC.config_from_dict(self.__config_dict)
def __config_param(self):
input_keys=self.__config_dict.keys()
geom_type_key=self.__tag+'.param.geom_type'
if geom_type_key in input_keys:
geom_type = self.__config_dict[geom_type_key]
else:
geom_type= 'Broken'
n_sect_key=self.__tag+'.param.n_sect'
if n_sect_key in input_keys:
n_sect = self.__config_dict[n_sect_key]
else:
n_sect = 20
self.__wing_param = Wing_param(self.__tag+'.param',geom_type=geom_type,n_sect=n_sect)
self.__wing_param.set_AoA_id(self.__AoA_id)
self.__wing_param.config_from_dict(self.__OC, self.__config_dict)
def __config_DLLM(self):
WARNING_MSG=self.WARNING_MSG+'__config_DLLM: '
input_keys=self.__config_dict.keys()
type_key = self.__tag+'.DLLM.type'
type = self.__config_dict[type_key]
if type not in self.POS_SOLVER:
print WARNING_MSG+'solver_type = '+str(type)+' not in '+str(self.POS_SOLVER)+'. Set to default solver_type = Solver'
type='Solver'
if type == 'Solver':
self.__DLLM_solver = DLLMSolver(self.__tag,self.__wing_param,self.__OC)
elif type == 'TargetCl':
self.__DLLM_solver = DLLMTargetCl(self.__tag,self.__wing_param,self.__OC)
target_Cl_key = self.__tag+'.DLLM.target_Cl'
target_Cl = self.__config_dict[target_Cl_key]
self.__DLLM_solver.set_target_Cl(target_Cl)
elif type == 'TargetLift':
self.__DLLM_solver = DLLMTargetLift(self.__tag,self.__wing_param,self.__OC)
target_Lift_key = self.__tag+'.DLLM.target_Lift'
target_Lift = self.__config_dict[target_Lift_key]
self.__DLLM_solver.set_target_Lift(target_Lift)
method_key = self.__tag+'.DLLM.method'
if method_key in input_keys:
method = self.__config_dict[method_key]
self.__DLLM_solver.set_method(method)
relax_factor_key = self.__tag+'.DLLM.relax_factor'
if relax_factor_key in input_keys:
relax_factor = self.__config_dict[relax_factor_key]
self.__DLLM_solver.set_relax_factor(relax_factor)
stop_residual_key = self.__tag+'.DLLM.stop_residual'
if stop_residual_key in input_keys:
stop_residual = self.__config_dict[stop_residual_key]
self.__DLLM_solver.set_stop_residual(stop_residual)
max_iterations_key = self.__tag+'.DLLM.max_iterations'
if max_iterations_key in input_keys:
max_iterations = self.__config_dict[max_iterations_key]
self.__DLLM_solver.set_max_iterations(max_iterations)
gamma_file_name_key = self.__tag+'.DLLM.gamma_file_name'
if gamma_file_name_key in input_keys:
gamma_file_name = self.__config_dict[gamma_file_name_key]
self.__DLLM_solver.set_gamma_file_name(gamma_file_name)
F_list_names_key = self.__tag+'.DLLM.F_list_names'
if F_list_names_key in input_keys:
F_list_names = self.__config_dict[F_list_names_key]
self.__DLLM_solver.set_F_list_names(F_list_names)
from DLLM.DLLMGeom.wing_param import Wing_param
from DLLM.DLLMKernel.DLLMSolver import DLLMSolver
from MDOTools.ValidGrad.FDValidGrad import FDValidGrad
from MDOTools.OC.operating_condition import OperatingCondition
import numpy
OC=OperatingCondition('cond1')
OC.set_Mach(0.6) #.7
OC.set_AoA(6.0) #3.
OC.set_altitude(10000.) #5000
OC.set_T0_deg(20.)
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',34.1)
wing_param.set_value('sweep',32.) #32.
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',5.4)#6.1
wing_param.set_value('break_chord',4.6)#4.6
wing_param.set_value('tip_chord',1.2)#1.5
wing_param.set_value('root_height',.98)#1.28
wing_param.set_value('break_height',0.7)#0.97
wing_param.set_value('tip_height',0.18)#0.33
wing_param.convert_to_design_variable('span',(10.,50.))
wing_param.convert_to_design_variable('sweep',(0.,40.))
wing_param.convert_to_design_variable('break_percent',(20.,40.))
wing_param.convert_to_design_variable('root_chord',(5.,7.))
wing_param.convert_to_design_variable('break_chord',(3.,5.))
def __init_wing_param(self):
OC=OperatingCondition('cond1')
OC.set_Mach(0.7)
OC.set_AoA(3.0)
OC.set_altitude(5000.)
OC.set_T0_deg(20.)
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',34.1)
wing_param.set_value('sweep',32.)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',6.1)
wing_param.set_value('break_chord',4.6)
wing_param.set_value('tip_chord',1.5)
wing_param.set_value('root_height',1.28)
wing_param.set_value('break_height',0.97)
wing_param.set_value('tip_height',0.33)
wing_param.convert_to_design_variable('span',(10.,50.))
wing_param.convert_to_design_variable('sweep',(0.,40.))
wing_param.convert_to_design_variable('break_percent',(20.,40.))
wing_param.convert_to_design_variable('root_chord',(5.,7.))
wing_param.convert_to_design_variable('break_chord',(3.,5.))
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()
return wing_param
def test_Wing_param_convert(self):
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',34.1)
wing_param.set_value('sweep',32.)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',6.1)
wing_param.set_value('break_chord',4.6)
wing_param.set_value('tip_chord',1.5)
wing_param.set_value('root_height',1.28)
wing_param.set_value('break_height',0.97)
wing_param.set_value('tip_height',0.33)
try:
wing_param.convert_to_design_variable('span',(10.,50.))
wing_param.convert_to_design_variable('sweep',(0.,40.))
wing_param.convert_to_design_variable('break_percent',(20.,40.))
wing_param.convert_to_design_variable('root_chord',(5.,7.))
wing_param.convert_to_design_variable('break_chord',(3.,5.))
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))
ok=True
except:
ok=False
assert(ok)
#
# http://github.com/TBD
#
from DLLM.DLLMGeom.wing_param import Wing_param
from MDOTools.OC.operating_condition import OperatingCondition
import numpy
import string
OC=OperatingCondition('cond1')
OC.set_altitude(3000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',34.1)
wing_param.set_value('sweep',0.)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',6.1)
wing_param.set_value('break_chord',4.6)
wing_param.set_value('tip_chord',1.5)
wing_param.set_value('root_height',1.28)
wing_param.set_value('break_height',0.97)
wing_param.set_value('tip_height',0.33)
wing_param.build_linear_airfoil(OC, AoA0=0., Cm0=-0.1, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
airfoils=wing_param.get_linked_airfoils()
#
# Imports
from DLLM.DLLMGeom.wing_param import Wing_param
from DLLM.DLLMKernel.DLLMSolver import DLLMSolver
from MDOTools.OC.operating_condition import OperatingCondition
OC = OperatingCondition("cond1")
OC.set_Mach(0.8)
OC.set_AoA(3.5)
OC.set_altitude(10000.0)
OC.set_T0_deg(15.0)
OC.set_P0(101325.0)
OC.set_humidity(0.0)
OC.compute_atmosphere()
wing_param = Wing_param("test_param", geom_type="Broken", n_sect=20)
wing_param.build_wing()
wing_param.set_value("span", 34.1) # 34.1
wing_param.set_value("sweep", 34.0)
wing_param.set_value("break_percent", 23.0) # 33.
wing_param.set_value("root_chord", 5.4) # 6.1
wing_param.set_value("break_chord", 4.6)
wing_param.set_value("tip_chord", 1.2) # 1.5
wing_param.set_value("root_height", 0.98)
wing_param.set_value("break_height", 0.70)
wing_param.set_value("tip_height", 0.18)
wing_param.convert_to_design_variable("span", (10.0, 50.0))
wing_param.convert_to_design_variable("sweep", (0.0, 40.0))
wing_param.convert_to_design_variable("break_percent", (20.0, 40.0))
wing_param.convert_to_design_variable("root_chord", (5.0, 7.0))
wing_param.convert_to_design_variable("break_chord", (3.0, 5.0))
class DLLMOpenMDAOComponent(Component):
# set up interface to the framework
# pylint: disable-msg=E1101
# Outputs of lifting line problem
"""OpenMDAO component for DLLM implementation
"""
Lift = Float(iotype='out', desc='Lift')
Drag = Float(iotype='out', desc='Drag')
Drag_Pressure = Float(iotype='out', desc='Drag_Pressure')
Drag_Induced = Float(iotype='out', desc='Drag_Induced')
Drag_Wave = Float(iotype='out', desc='Drag_Wave')
Drag_Friction = Float(iotype='out', desc='Drag_Friction')
Cd = Float(iotype='out', desc='Cd')
Cdp = Float(iotype='out', desc='Cdp')
Cdi = Float(iotype='out', desc='Cdi')
Cdw = Float(iotype='out', desc='Cdw')
Cdf = Float(iotype='out', desc='Cdf')
Cl = Float(iotype='out', desc='Cl')
LoD = Float(iotype='out', desc='LoD')
Sref = Float(iotype='out', desc='Sref')
# Design variables of lifting line problem
rtwist = Array([], desc='rtwist', iotype="in")
span = Float(desc='span', default_value=34., iotype="in")
sweep = Float(desc='sweep', default_value=34., iotype="in")
break_percent = Float(desc='break_percent', default_value=33., iotype="in")
root_chord = Float(desc='root_chord', default_value=6.1, iotype="in")
break_chord = Float(desc='break_chord', default_value=4.6, iotype="in")
tip_chord = Float(desc='tip_chord', default_value=1.5, iotype="in")
root_height = Float(desc='root_height', default_value=1.28, iotype="in")
break_height = Float(desc='break_height', default_value=0.97, iotype="in")
tip_height = Float(desc='tip_height', default_value=0.33, iotype="in")
# Operating conditions variables
Mach = Float(iotype='in', default_value=0.7, desc='Mach')
altitude = Float(iotype='in', default_value=10000., desc='Altitude')
T0 = Float(iotype='in',default_value=OperatingCondition.T0,
desc='Ground ISA ref Temperature')
P0 = Float(iotype='in',default_value=OperatingCondition.P0,
desc='Ground ISA ref Pressure')
def __init__(self,Target_Lift, N = 10, verbose=0):
"""Initialization of DLLM component.
DLLM component use target lift capability of DLLM kernel
@param Target_Lift : the targeted lift value (float)
@param N : integer. Number of discrete section on 1/2 wing
@param verbose : integer : verbosity level
"""
try :
float(Target_Lift)
except:
raise ValueError('You MUST define a float target lift value, get '+str(Target_Lift)+' instead.')
self.Target_Lift = Target_Lift
self.N = N
self.OC = None
self.rtwist = np.zeros(N)
self.__display_wing_param = True
self.__verbose = verbose
self.__wing_param = None
super(DLLMOpenMDAOComponent, self).__init__()
self.OC = OperatingCondition(tag='DLLMOC', atmospheric_model='ISA')
self.__set_OC_values()
self.__set_wing_param()
self.__DLLM = DLLMTargetLift('test', self.__wing_param,
self.OC, verbose=self.__verbose)
self.__DLLM.set_target_Lift(Target_Lift)
self.__DLLM.run_direct()
self.__DLLM.run_post()
def __set_wing_param(self, wing_param_name='test_param'):
"""Method for wing parameters setting : design variables initial values and bounds
@param wing_param_name : wing parametrization names
"""
self.__set_wing_param_values(wing_param_name=wing_param_name)
self.__set_wing_param_bounds()
self.__wing_param.build_linear_airfoil(self.OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
self.__wing_param.build_airfoils_from_ref()
self.__wing_param.update()
if self.__display_wing_param:
self.__display_wing_param = False
print self.__wing_param
def __set_wing_param_values(self, wing_param_name='test_param'):
"""Method for wing parameters variables setting
@param wing_param_name : wing parametrization names
"""
self.__wing_param = Wing_param(wing_param_name,
geom_type='Broken', n_sect=self.N * 2)
self.__wing_param.build_wing()
for i in xrange(self.N):
self.__wing_param.set_value('rtwist%s' % i, 0.)
for param in Wing_param.DISCRETE_ATTRIBUTES_LIST:
self.__wing_param.set_value(param, getattr(self, param))
def __set_wing_param_bounds(self):
"""Method for desing variables bounds settings
Values are set to inf/-inf in DLLM component and their 'real' bounds
are defined when optimization problem is set
"""
for i in xrange(self.N):
self.__wing_param.convert_to_design_variable(
'rtwist%s' % i, (-float('inf'), float('inf')))
for param in Wing_param.DISCRETE_ATTRIBUTES_LIST:
self.__wing_param.convert_to_design_variable(param, (-float('inf'), float('inf')))
return
def __set_OC_values(self):
""" Set default operating conditions"""
self.OC.set_Mach(self.Mach)
self.OC.set_altitude(self.altitude)
self.OC.set_T0(self.T0)
self.OC.set_P0(self.P0)
self.OC.set_humidity(0.)
self.OC.compute_atmosphere()
def __update_wing_parame_values(self):
for dv_id in self.__wing_param.get_dv_id_list():
if dv_id.startswith('rtwist'):
i_twist = int(dv_id.replace('rtwist', ''))
self.__wing_param.set_value(dv_id, self.rtwist[i_twist])
else:
self.__wing_param.set_value(dv_id,getattr(self,dv_id))
self.__wing_param.build_linear_airfoil(self.OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
self.__set_wing_param_bounds()
self.__wing_param.build_airfoils_from_ref()
self.__wing_param.update()
return
def execute(self):
""" Perform a DLLM computation with the """
self.__update_wing_parame_values()
self.__set_OC_values()
self.__DLLM.set_target_Lift(self.Target_Lift)
self.__DLLM.run_direct()
self.__DLLM.run_post()
output = self.__DLLM.get_F_list()
for f, f_name in zip(output, self.__DLLM.get_F_list_names()):
setattr(self, f_name, f)
def list_deriv_vars(self):
"""specify the inputs and outputs where derivatives are defined
Specific treatment for twist : defined as rtwist0, rtwist1,... in DLLM
but as an array rtwist in openmdao component"""
out_dvid = []
for dv_id in self.__wing_param.get_dv_id_list():
if dv_id.startswith('rtwist0'):
out_dvid.append('rtwist')
elif not dv_id.startswith('rtwist'):
out_dvid.append(dv_id)
return tuple(out_dvid), tuple(self.__DLLM.get_F_list_names())
def provideJ(self):
"""Calculate the Jacobian according inputs and outputs"""
self.__DLLM.run_adjoint()
return np.array(self.__DLLM.get_dF_list_dchi())
def get_F_list(self):
return self.__DLLM.get_F_list()
def get_F_list_names(self):
return self.__DLLM.get_F_list_names()
def get_dv_array(self):
return self.__wing_param.get_dv_array()
def get_dv_id_list(self):
return self.__wing_param.get_dv_id_list()
def get_dv_info_list(self):
return self.__wing_param.get_dv_info_list()
def get_dv_value(self,dv_id):
return self.get_dv_array()[self.get_dv_id_list().index(dv_id)]
from DLLM.DLLMGeom.wing_param import Wing_param
from DLLM.DLLMKernel.DLLMSolver import DLLMSolver
from MDOTools.ValidGrad.FDValidGrad import FDValidGrad
from MDOTools.OC.operating_condition import OperatingCondition
import numpy
OC = OperatingCondition('cond1')
OC.set_Mach(0.6) #.7
OC.set_AoA(6.0) #3.
OC.set_altitude(10000.) #5000
OC.set_T0_deg(20.)
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param = Wing_param('test_param', geom_type='Broken', n_sect=20)
wing_param.build_wing()
wing_param.set_value('span', 34.1)
wing_param.set_value('sweep', 32.) #32.
wing_param.set_value('break_percent', 33.)
wing_param.set_value('root_chord', 5.4) #6.1
wing_param.set_value('break_chord', 4.6) #4.6
wing_param.set_value('tip_chord', 1.2) #1.5
wing_param.set_value('root_height', .98) #1.28
wing_param.set_value('break_height', 0.7) #0.97
wing_param.set_value('tip_height', 0.18) #0.33
wing_param.convert_to_design_variable('span', (10., 50.))
wing_param.convert_to_design_variable('sweep', (0., 40.))
wing_param.convert_to_design_variable('break_percent', (20., 40.))
wing_param.convert_to_design_variable('root_chord', (5., 7.))
wing_param.convert_to_design_variable('break_chord', (3., 5.))
from DLLM.DLLMGeom.wing_param import Wing_param
from DLLM.DLLMKernel.DLLMSolver import DLLMSolver
from MDOTools.ValidGrad.FDValidGrad import FDValidGrad
from MDOTools.OC.operating_condition import OperatingCondition
import numpy
OC=OperatingCondition('cond1')
OC.set_Mach(0.8)
OC.set_AoA(3.5)
OC.set_altitude(10000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',34.1)
wing_param.set_value('sweep',34.)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',6.1)
wing_param.set_value('break_chord',4.6)
wing_param.set_value('tip_chord',1.5)
wing_param.set_value('root_height',1.28)
wing_param.set_value('break_height',0.97)
wing_param.set_value('tip_height',0.33)
wing_param.convert_to_design_variable('span',(10.,50.))
wing_param.convert_to_design_variable('sweep',(0.,40.))
wing_param.convert_to_design_variable('break_percent',(20.,40.))
wing_param.convert_to_design_variable('root_chord',(5.,7.))
wing_param.convert_to_design_variable('break_chord',(3.,5.))
import string
OC=OperatingCondition('cond1',atmospheric_model='simple')
#OC.set_Mach(0.8)
#OC.set_Mach(0.6)
#OC.set_AoA(3.5)
AoA_list = [float(xx) for xx in range(0, 10)]
Mach_list = [float(xx)/10. for xx in range(3, 9)]
Mach_list = [0.3,0.6,0.8]
OC.set_altitude(10000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',2.392)
#wing_param.set_value('sweep',34.)
wing_param.set_value('sweep',26.7)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',0.806)
wing_param.set_value('break_chord',0.689)
wing_param.set_value('tip_chord',0.451)
#wing_param.set_value('root_height',1.28)
wing_param.set_value('root_height',0.0782)
#wing_param.set_value('break_height',0.97)
wing_param.set_value('break_height',0.0668)
#wing_param.set_value('tip_height',0.33)
wing_param.set_value('tip_height',0.0438)
#wing_param.convert_to_design_variable('span',10.,50.)
#
# http://github.com/TBD
#
from DLLM.DLLMGeom.wing_param import Wing_param
from MDOTools.OC.operating_condition import OperatingCondition
import numpy
import string
OC = OperatingCondition("cond1")
OC.set_altitude(3000.0)
OC.set_T0_deg(15.0)
OC.set_P0(101325.0)
OC.set_humidity(0.0)
wing_param = Wing_param("test_param", geom_type="Broken", n_sect=20)
wing_param.build_wing()
wing_param.set_value("span", 34.1)
wing_param.set_value("sweep", 0.0)
wing_param.set_value("break_percent", 33.0)
wing_param.set_value("root_chord", 6.1)
wing_param.set_value("break_chord", 4.6)
wing_param.set_value("tip_chord", 1.5)
wing_param.set_value("root_height", 1.28)
wing_param.set_value("break_height", 0.97)
wing_param.set_value("tip_height", 0.33)
wing_param.build_linear_airfoil(OC, AoA0=0.0, Cm0=-0.1, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
airfoils = wing_param.get_linked_airfoils()
#
from DLLM.DLLMGeom.wing_param import Wing_param
from MDOTools.OC.operating_condition import OperatingCondition
import numpy
import string
OC=OperatingCondition('cond1')
OC.set_altitude(3000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
nsect=50
wing_param=Wing_param('test_param',geom_type='Elliptic',n_sect=nsect)
wing_param.set_distrib_type('cos_law')
wing_param.build_wing()
wing_param.set_value('span',40.)
wing_param.set_value('root_chord',4.)
wing_param.set_value('root_height',0.0)
wing_param.set_value('tip_height',0.0)
wing_param.build_linear_airfoil(OC, AoA0=0., Cm0=-0.1, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
airfoils=wing_param.get_linked_airfoils()
Cla=airfoils[24].ClAlpha(0.0,0.3)
print "Cla=",Cla
OC=OperatingCondition('cond1')
#OC.set_Mach(0.8)
#OC.set_Mach(0.6)
#OC.set_AoA(3.5)
AoA_list = [float(xx) for xx in range(0, 10)]
#AoA_list=[9.]
#Mach_list = [float(xx)/10. for xx in range(3, 9)]
Mach_list = [0.2]#,0.6,0.8]
OC.set_altitude(10000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=50)
wing_param.set_distrib_type('cos_law')
wing_param.build_wing()
wing_param.set_value('span',30.)
#wing_param.set_value('sweep',34.)
wing_param.set_value('sweep',0.)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',1.)
wing_param.set_value('break_chord',1.)
wing_param.set_value('tip_chord',1.)
#wing_param.set_value('root_height',1.28)
wing_param.set_value('root_height',0.0)
#wing_param.set_value('break_height',0.97)
wing_param.set_value('break_height',0.0)
#wing_param.set_value('tip_height',0.33)
wing_param.set_value('tip_height',0.0)
def test_Wing_param_set_value(self):
"""
test set value for Wing_param
"""
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
try:
wing_param.set_value('span',34.1)
wing_param.set_value('sweep',32.)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',6.1)
wing_param.set_value('break_chord',4.6)
wing_param.set_value('tip_chord',1.5)
wing_param.set_value('root_height',1.28)
wing_param.set_value('break_height',0.97)
wing_param.set_value('tip_height',0.33)
ok=True
except:
ok=False
assert(ok)
#
from DLLM.DLLMGeom.wing_param import Wing_param
from MDOTools.OC.operating_condition import OperatingCondition
import numpy
import string
OC=OperatingCondition('cond1')
OC.set_altitude(10000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
nsect=50
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=nsect)
wing_param.build_wing()
wing_param.set_value('span',30.)
#wing_param.set_value('sweep',34.)
wing_param.set_value('sweep',0.)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',1.0)
wing_param.set_value('break_chord',1.0)
wing_param.set_value('tip_chord',1.0)
#wing_param.set_value('root_height',1.28)
wing_param.set_value('root_height',0.1)
#wing_param.set_value('break_height',0.97)
wing_param.set_value('break_height',0.1)
#wing_param.set_value('tip_height',0.33)
wing_param.set_value('tip_height',0.1)
#wing_param.convert_to_design_variable('span',10.,50.)
def test_Wing_param_convert(self):
wing_param = Wing_param('test_param', geom_type='Broken', n_sect=20)
wing_param.build_wing()
wing_param.set_value('span', 34.1)
wing_param.set_value('sweep', 32.)
wing_param.set_value('break_percent', 33.)
wing_param.set_value('root_chord', 6.1)
wing_param.set_value('break_chord', 4.6)
wing_param.set_value('tip_chord', 1.5)
wing_param.set_value('root_height', 1.28)
wing_param.set_value('break_height', 0.97)
wing_param.set_value('tip_height', 0.33)
try:
wing_param.convert_to_design_variable('span', (10., 50.))
wing_param.convert_to_design_variable('sweep', (0., 40.))
wing_param.convert_to_design_variable('break_percent', (20., 40.))
wing_param.convert_to_design_variable('root_chord', (5., 7.))
wing_param.convert_to_design_variable('break_chord', (3., 5.))
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))
ok = True
except:
ok = False
assert (ok)
def test_Wing_param_update(self):
OC=self.__init_OC()
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',34.1)
wing_param.set_value('sweep',32.)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',6.1)
wing_param.set_value('break_chord',4.6)
wing_param.set_value('tip_chord',1.5)
wing_param.set_value('root_height',1.28)
wing_param.set_value('break_height',0.97)
wing_param.set_value('tip_height',0.33)
wing_param.convert_to_design_variable('span',(10.,50.))
wing_param.convert_to_design_variable('sweep',(0.,40.))
wing_param.convert_to_design_variable('break_percent',(20.,40.))
wing_param.convert_to_design_variable('root_chord',(5.,7.))
wing_param.convert_to_design_variable('break_chord',(3.,5.))
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()
try:
wing_param.update()
ok=True
except:
ok=False
assert(ok)
def __init_wing_param(self):
OC = OperatingCondition('cond1')
OC.set_Mach(0.7)
OC.set_AoA(3.0)
OC.set_altitude(5000.)
OC.set_T0_deg(20.)
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param = Wing_param('test_param', geom_type='Broken', n_sect=20)
wing_param.build_wing()
wing_param.set_value('span', 34.1)
wing_param.set_value('sweep', 32.)
wing_param.set_value('break_percent', 33.)
wing_param.set_value('root_chord', 6.1)
wing_param.set_value('break_chord', 4.6)
wing_param.set_value('tip_chord', 1.5)
wing_param.set_value('root_height', 1.28)
wing_param.set_value('break_height', 0.97)
wing_param.set_value('tip_height', 0.33)
wing_param.convert_to_design_variable('span', (10., 50.))
wing_param.convert_to_design_variable('sweep', (0., 40.))
wing_param.convert_to_design_variable('break_percent', (20., 40.))
wing_param.convert_to_design_variable('root_chord', (5., 7.))
wing_param.convert_to_design_variable('break_chord', (3., 5.))
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()
return wing_param
#
# Imports
from DLLM.DLLMGeom.wing_param import Wing_param
from DLLM.DLLMKernel.DLLMSolver import DLLMSolver
from MDOTools.OC.operating_condition import OperatingCondition
OC=OperatingCondition('cond1')
OC.set_Mach(0.3)
OC.set_AoA(4.)
OC.set_altitude(1000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',2.392) #34.1
wing_param.set_value('sweep',26.7)
wing_param.set_value('break_percent',33.) #33.
wing_param.set_value('root_chord',0.806) #6.1
wing_param.set_value('break_chord',0.689)
wing_param.set_value('tip_chord',0.451) #1.5
wing_param.set_value('root_height',0.0782)
wing_param.set_value('break_height',0.0668)
wing_param.set_value('tip_height',0.0438)
wing_param.convert_to_design_variable('span',(10.,50.))
wing_param.convert_to_design_variable('sweep',(0.,40.))
wing_param.convert_to_design_variable('break_percent',(20.,40.))
wing_param.convert_to_design_variable('root_chord',(5.,7.))
wing_param.convert_to_design_variable('break_chord',(3.,5.))
OC = OperatingCondition('cond1')
#OC.set_Mach(0.8)
#OC.set_Mach(0.6)
#OC.set_AoA(3.5)
AoA_list = [float(xx) for xx in range(0, 10)]
AoA_list = [9.]
#Mach_list = [float(xx)/10. for xx in range(3, 9)]
Mach_list = [0.2] #,0.6,0.8]
OC.set_altitude(10000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
wing_param = Wing_param('test_param', geom_type='Rectangular', n_sect=50)
wing_param.build_wing()
wing_param.set_value('span', 40.)
#wing_param.set_value('sweep',34.)
wing_param.set_value('sweep', 0.)
wing_param.set_value('root_chord', 1.0)
wing_param.set_value('root_height', 0.1)
wing_param.set_value('tip_height', 0.1)
wing_param.build_linear_airfoil(OC,
AoA0=0.,
Cm0=-0.1,
Ka=0.75,
set_as_ref=True)
#wing_param.build_meta_airfoil(OC, '../ONERA_D.xml', relative_thickness=.09, camber=0, Sref=1., Lref=1., sweep=.0, set_as_ref=True)
wing_param.build_airfoils_from_ref()
import string
OC=OperatingCondition('cond1')
#OC.set_Mach(0.8)
#OC.set_Mach(0.6)
#OC.set_AoA(3.5)
AoA_list = [float(xx) for xx in range(0, 10)]
#Mach_list = [float(xx)/10. for xx in range(3, 9)]
Mach_list = [0.3]#,0.6,0.8]
OC.set_altitude(3000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',34.1)
wing_param.set_value('sweep',0.)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',6.1)
wing_param.set_value('break_chord',4.6)
wing_param.set_value('tip_chord',1.5)
wing_param.set_value('root_height',1.28)
wing_param.set_value('break_height',0.97)
wing_param.set_value('tip_height',0.33)
wing_param.build_linear_airfoil(OC, AoA0=0., Cm0=-0.1, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
print 'AR=',wing_param.get_AR()
#
# Imports
from DLLM.DLLMGeom.wing_param import Wing_param
from DLLM.DLLMKernel.DLLMSolver import DLLMSolver
from MDOTools.OC.operating_condition import OperatingCondition
OC = OperatingCondition('cond1')
OC.set_Mach(0.3)
OC.set_AoA(4.)
OC.set_altitude(1000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param = Wing_param('test_param', geom_type='Broken', n_sect=20)
wing_param.build_wing()
wing_param.set_value('span', 2.392) #34.1
wing_param.set_value('sweep', 26.7)
wing_param.set_value('break_percent', 33.) #33.
wing_param.set_value('root_chord', 0.806) #6.1
wing_param.set_value('break_chord', 0.689)
wing_param.set_value('tip_chord', 0.451) #1.5
wing_param.set_value('root_height', 0.0782)
wing_param.set_value('break_height', 0.0668)
wing_param.set_value('tip_height', 0.0438)
wing_param.convert_to_design_variable('span', (10., 50.))
wing_param.convert_to_design_variable('sweep', (0., 40.))
wing_param.convert_to_design_variable('break_percent', (20., 40.))
wing_param.convert_to_design_variable('root_chord', (5., 7.))
wing_param.convert_to_design_variable('break_chord', (3., 5.))
def test_Wing_param_linear_airfoil(self):
OC = self.__init_OC()
wing_param = Wing_param('test_param', geom_type='Broken', n_sect=20)
wing_param.build_wing()
wing_param.set_value('span', 34.1)
wing_param.set_value('sweep', 32.)
wing_param.set_value('break_percent', 33.)
wing_param.set_value('root_chord', 6.1)
wing_param.set_value('break_chord', 4.6)
wing_param.set_value('tip_chord', 1.5)
wing_param.set_value('root_height', 1.28)
wing_param.set_value('break_height', 0.97)
wing_param.set_value('tip_height', 0.33)
wing_param.convert_to_design_variable('span', (10., 50.))
wing_param.convert_to_design_variable('sweep', (0., 40.))
wing_param.convert_to_design_variable('break_percent', (20., 40.))
wing_param.convert_to_design_variable('root_chord', (5., 7.))
wing_param.convert_to_design_variable('break_chord', (3., 5.))
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))
try:
wing_param.build_linear_airfoil(OC,
AoA0=-2.,
Cm0=-0.1,
set_as_ref=True)
wing_param.build_airfoils_from_ref()
ok = True
except:
ok = False
assert (ok)
#
# http://github.com/TBD
#
from DLLM.DLLMGeom.wing_param import Wing_param
from MDOTools.OC.operating_condition import OperatingCondition
import numpy
import string
OC=OperatingCondition('cond1',atmospheric_model='simple')
OC.set_altitude(10000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',2.392)
#wing_param.set_value('sweep',34.)
wing_param.set_value('sweep',26.7)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',0.806)
wing_param.set_value('break_chord',0.689)
wing_param.set_value('tip_chord',0.451)
#wing_param.set_value('root_height',1.28)
wing_param.set_value('root_height',0.0782)
#wing_param.set_value('break_height',0.97)
wing_param.set_value('break_height',0.0668)
#wing_param.set_value('tip_height',0.33)
wing_param.set_value('tip_height',0.0438)
#wing_param.convert_to_design_variable('span',10.,50.)
def test_Wing_param_instantiation(self):
"""
test class instantiation
"""
wing_param = Wing_param('test_param', geom_type='Broken', n_sect=20)
assert (wing_param is not None)
from MDOTools.ValidGrad.FDValidGrad import FDValidGrad
from DLLM.DLLMGeom.wing_param import Wing_param
from DLLM.DLLMKernel.DLLMSolver import DLLMSolver
from MDOTools.OC.operating_condition import OperatingCondition
import numpy
OC = OperatingCondition("cond1")
OC.set_Mach(0.8)
OC.set_AoA(3.5)
OC.set_altitude(10000.0)
OC.set_T0_deg(15.0)
OC.set_P0(101325.0)
OC.set_humidity(0.0)
OC.compute_atmosphere()
wing_param = Wing_param("test_param", geom_type="Broken", n_sect=20)
wing_param.build_wing()
wing_param.set_value("span", 34.1)
wing_param.set_value("sweep", 34.0)
wing_param.set_value("break_percent", 33.0)
wing_param.set_value("root_chord", 6.1)
wing_param.set_value("break_chord", 4.6)
wing_param.set_value("tip_chord", 1.5)
wing_param.set_value("root_height", 1.28)
wing_param.set_value("break_height", 0.97)
wing_param.set_value("tip_height", 0.33)
wing_param.convert_to_design_variable("span", (0.0, 50.0))
wing_param.convert_to_design_variable("sweep", (0.0, 40.0))
wing_param.convert_to_design_variable("break_percent", (20.0, 40.0))
wing_param.convert_to_design_variable("root_chord", (5.0, 7.0))
wing_param.convert_to_design_variable("break_chord", (3.0, 5.0))
def test_Wing_param_set_value(self):
"""
test set value for Wing_param
"""
wing_param = Wing_param('test_param', geom_type='Broken', n_sect=20)
wing_param.build_wing()
try:
wing_param.set_value('span', 34.1)
wing_param.set_value('sweep', 32.)
wing_param.set_value('break_percent', 33.)
wing_param.set_value('root_chord', 6.1)
wing_param.set_value('break_chord', 4.6)
wing_param.set_value('tip_chord', 1.5)
wing_param.set_value('root_height', 1.28)
wing_param.set_value('break_height', 0.97)
wing_param.set_value('tip_height', 0.33)
ok = True
except:
ok = False
assert (ok)
from DLLM.DLLMGeom.wing_param import Wing_param
from DLLM.DLLMKernel.DLLMTargetCl import DLLMTargetCl
from MDOTools.OC.operating_condition import OperatingCondition
import numpy
import sys
OC=OperatingCondition('cond1')
OC.set_Mach(0.3)
OC.set_AoA(0.)
OC.set_altitude(3000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',3.)
wing_param.set_value('sweep',30.)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',1.0)
wing_param.set_value('break_chord',1.0)
wing_param.set_value('tip_chord',1.0)
wing_param.set_value('root_height',0.15)
wing_param.set_value('break_height',0.15)
wing_param.set_value('tip_height',0.15)
wing_param.build_linear_airfoil(OC, AoA0=0., Cm0=0.0, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
print wing_param
#
# Imports
from DLLM.DLLMGeom.wing_param import Wing_param
from DLLM.DLLMKernel.DLLMSolver import DLLMSolver
from MDOTools.OC.operating_condition import OperatingCondition
OC=OperatingCondition('cond1')
OC.set_Mach(0.4)
OC.set_AoA(3.5)
OC.set_altitude(5000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',34.1) #34.1
wing_param.set_value('sweep',34.)
wing_param.set_value('break_percent',23.) #33.
wing_param.set_value('root_chord',5.4) #6.1
wing_param.set_value('break_chord',4.6)
wing_param.set_value('tip_chord',1.2) #1.5
wing_param.set_value('root_height',.98)
wing_param.set_value('break_height',0.70)
wing_param.set_value('tip_height',0.18)
wing_param.convert_to_design_variable('span',(10.,50.))
wing_param.convert_to_design_variable('sweep',(0.,40.))
wing_param.convert_to_design_variable('break_percent',(20.,40.))
wing_param.convert_to_design_variable('root_chord',(5.,7.))
wing_param.convert_to_design_variable('break_chord',(3.,5.))
import string
OC = OperatingCondition('cond1', atmospheric_model='simple')
#OC.set_Mach(0.8)
#OC.set_Mach(0.6)
#OC.set_AoA(3.5)
AoA_list = [float(xx) for xx in range(0, 10)]
#Mach_list = [float(xx)/10. for xx in range(3, 9)]
Mach_list = [0.3, 0.6, 0.8]
OC.set_altitude(10000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
wing_param = Wing_param('test_param', geom_type='Broken', n_sect=20)
wing_param.build_wing()
wing_param.set_value('span', 2.392)
#wing_param.set_value('sweep',34.)
wing_param.set_value('sweep', 26.7)
wing_param.set_value('break_percent', 33.)
wing_param.set_value('root_chord', 0.806)
wing_param.set_value('break_chord', 0.689)
wing_param.set_value('tip_chord', 0.451)
#wing_param.set_value('root_height',1.28)
wing_param.set_value('root_height', 0.0782)
#wing_param.set_value('break_height',0.97)
wing_param.set_value('break_height', 0.0668)
#wing_param.set_value('tip_height',0.33)
wing_param.set_value('tip_height', 0.0438)
#wing_param.convert_to_design_variable('span',10.,50.)
from MDOTools.ValidGrad.FDValidGrad import FDValidGrad
from DLLM.DLLMGeom.wing_param import Wing_param
from DLLM.DLLMKernel.DLLMSolver import DLLMSolver
from MDOTools.OC.operating_condition import OperatingCondition
import numpy
OC = OperatingCondition('cond1')
OC.set_Mach(0.8)
OC.set_AoA(3.5)
OC.set_altitude(10000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param = Wing_param('test_param', geom_type='Broken', n_sect=20)
wing_param.build_wing()
wing_param.set_value('span', 34.1)
wing_param.set_value('sweep', 34.)
wing_param.set_value('break_percent', 33.)
wing_param.set_value('root_chord', 6.1)
wing_param.set_value('break_chord', 4.6)
wing_param.set_value('tip_chord', 1.5)
wing_param.set_value('root_height', 1.28)
wing_param.set_value('break_height', 0.97)
wing_param.set_value('tip_height', 0.33)
wing_param.convert_to_design_variable('span', (0., 50.))
wing_param.convert_to_design_variable('sweep', (0., 40.))
wing_param.convert_to_design_variable('break_percent', (20., 40.))
wing_param.convert_to_design_variable('root_chord', (5., 7.))
wing_param.convert_to_design_variable('break_chord', (3., 5.))
OC=OperatingCondition('cond1')
#OC.set_Mach(0.8)
#OC.set_Mach(0.6)
#OC.set_AoA(3.5)
AoA_list = [float(xx) for xx in range(0, 10)]
AoA_list = [9.]
#Mach_list = [float(xx)/10. for xx in range(3, 9)]
Mach_list = [0.2]#,0.6,0.8]
OC.set_altitude(10000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
wing_param=Wing_param('test_param',geom_type='Rectangular',n_sect=50)
wing_param.build_wing()
wing_param.set_value('span',40.)
#wing_param.set_value('sweep',34.)
wing_param.set_value('sweep',0.)
wing_param.set_value('root_chord',1.0)
wing_param.set_value('root_height',0.1)
wing_param.set_value('tip_height',0.1)
wing_param.build_linear_airfoil(OC, AoA0=0., Cm0=-0.1, Ka=0.75, set_as_ref=True)
#wing_param.build_meta_airfoil(OC, '../ONERA_D.xml', relative_thickness=.09, camber=0, Sref=1., Lref=1., sweep=.0, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
print wing_param
from DLLM.DLLMKernel.DLLMTargetCl import DLLMTargetCl
from MDOTools.OC.operating_condition import OperatingCondition
from MDOTools.ValidGrad.FDValidGrad import FDValidGrad
import numpy
import sys
OC=OperatingCondition('cond1')
OC.set_Mach(0.3)
OC.set_AoA(0.)
OC.set_altitude(3000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',40.)
wing_param.set_value('sweep',0.)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',1.0)
wing_param.set_value('break_chord',1.0)
wing_param.set_value('tip_chord',1.0)
wing_param.set_value('root_height',0.15)
wing_param.set_value('break_height',0.15)
wing_param.set_value('tip_height',0.15)
wing_param.build_linear_airfoil(OC, AoA0=0., Cm0=0.0, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
print wing_param
def __init_wing_param(self):
OC = OperatingCondition('cond1')
OC.set_Mach(0.8)
OC.set_AoA(3.5)
OC.set_altitude(10000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param = Wing_param('test_param', geom_type='Broken', n_sect=20)
wing_param.build_wing()
wing_param.set_value('span', 34.1)
wing_param.set_value('sweep', 34.)
wing_param.set_value('break_percent', 33.)
wing_param.set_value('root_chord', 6.1)
wing_param.set_value('break_chord', 4.6)
wing_param.set_value('tip_chord', 1.5)
wing_param.set_value('root_height', 1.28)
wing_param.set_value('break_height', 0.97)
wing_param.set_value('tip_height', 0.33)
wing_param.convert_to_design_variable('span', (10., 50.))
wing_param.convert_to_design_variable('sweep', (0., 40.))
wing_param.convert_to_design_variable('break_percent', (20., 40.))
wing_param.convert_to_design_variable('root_chord', (5., 7.))
wing_param.convert_to_design_variable('break_chord', (3., 5.))
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_meta_airfoil(OC,
'../examples/MetaModelFixed.xml',
relative_thickness=.12,
camber=0.,
Sref=1.,
Lref=1.,
sweep=.0,
set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
return OC, wing_param