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_linear_airfoil(OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
return OC,wing_param
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 __init_OC(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()
return OC
def __init_OC(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()
return OC
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_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()
return OC,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
DLLM.run_post()
output = DLLM.get_F_list()
F_list_names = DLLM.get_F_list_names()
return output, F_list_names
def set_polar_file(OC, polar_name):
with open(polar_name, 'w') as f:
# Header is no up to date!!!
header = '# polar for Mach ='+str(OC.get_Mach())
f.write(header+'\n')
f.closed
def add_to_polar(polar_name, values, tags, i):
with open(polar_name, 'a') as f:
if i == 0:
line = "# "
line+=string.join(tags,'\t')
f.write(line+'\n')
line = ''
for param in values:
line = line+'%.10E ' % param
f.write(line+'\n')
f.closed
for M in Mach_list:
OC.set_Mach(M)
OC.compute_atmosphere()
RunPolar(wing_param,OC, AoA_list, 'WingSweep0')
F_list_names = DLLM.get_F_list_names()
return output, F_list_names
def set_polar_file(OC, polar_name):
with open(polar_name, 'w') as f:
# Header is no up to date!!!
header = '# polar for Mach =' + str(OC.get_Mach())
f.write(header + '\n')
f.closed
def add_to_polar(polar_name, values, tags, i):
with open(polar_name, 'a') as f:
if i == 0:
line = "# "
line += string.join(tags, '\t')
f.write(line + '\n')
line = ''
for param in values:
line = line + '%.10E ' % param
f.write(line + '\n')
f.closed
for M in Mach_list:
OC.set_Mach(M)
OC.compute_atmosphere()
RunPolar(wing_param, OC, AoA_list, 'SimpleOneraM6')
# GNU General Public License for more details.
#
# You should have received a copy of the GNU General Public License
# along with this program; if not, write to the Free Software
# Foundation, Inc., 51 Franklin Street, Fifth Floor, Boston, MA 02110-1301, USA.
#
# http://github.com/TBD
#
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)
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)]
# GNU General Public License for more details.
#
# You should have received a copy of the GNU General Public License
# along with this program; if not, write to the Free Software
# Foundation, Inc., 51 Franklin Street, Fifth Floor, Boston, MA 02110-1301, USA.
#
# http://github.com/TBD
#
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
# but WITHOUT ANY WARRANTY; without even the implied warranty of
# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
# GNU General Public License for more details.
#
# You should have received a copy of the GNU General Public License
# along with this program; if not, write to the Free Software
# Foundation, Inc., 51 Franklin Street, Fifth Floor, Boston, MA 02110-1301, USA.
#
# http://github.com/TBD
#
from MDOTools.ValidGrad.FDValidGrad import FDValidGrad
from DLLM.DLLMGeom.wing_param import Wing_param
from MDOTools.OC.operating_condition import OperatingCondition
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)
# GNU General Public License for more details.
#
# You should have received a copy of the GNU General Public License
# along with this program; if not, write to the Free Software
# Foundation, Inc., 51 Franklin Street, Fifth Floor, Boston, MA 02110-1301, USA.
#
# http://github.com/TBD
#
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
# but WITHOUT ANY WARRANTY; without even the implied warranty of
# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
# GNU General Public License for more details.
#
# You should have received a copy of the GNU General Public License
# along with this program; if not, write to the Free Software
# Foundation, Inc., 51 Franklin Street, Fifth Floor, Boston, MA 02110-1301, USA.
#
# http://github.com/TBD
#
from MDOTools.ValidGrad.FDValidGrad import FDValidGrad
from DLLM.DLLMGeom.wing_param import Wing_param
from MDOTools.OC.operating_condition import OperatingCondition
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)
import numpy as np
from DLLM.polarManager.RefCTAAirfoil import RefCTAAirfoil
from MDOTools.OC.operating_condition import OperatingCondition
#Mach = 0.79
#Cl = 0.21
#Altitude 35000 ft
OC=OperatingCondition('Cond_RefCTA',atmospheric_model='ISA')
OC.set_Mach(0.79)
OC.set_AoA(3.5)
OC.set_altitude_feet(35000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
print OC
RefCTA_AF = RefCTAAirfoil(OC)
RefCTA_AF.set_y_def_list([0.,1.520, 3.800, 6.080, 9.120, 12.160, 15.200, 18.240, 19.000])
RefCTA_AF.set_file_def_list(['section0.dat','section1.dat','section2.dat','section3.dat','section4.dat','section5.dat','section6.dat','section7.dat','section8.dat'])
RefCTA_AF.init_interpolators()
RefCTA_AF.set_y_pos(-5.1)
RefCTA_AF.init_interp_factors()
AoA = 2.*np.pi/180.
RefCTA_AF.compute(AoA, 0.79)
#
# You should have received a copy of the GNU General Public License
# along with this program; if not, write to the Free Software
# Foundation, Inc., 51 Franklin Street, Fifth Floor, Boston, MA 02110-1301, USA.
#
# http://github.com/TBD
#
from MDOTools.ValidGrad.FDValidGrad import FDValidGrad
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)
#
# You should have received a copy of the GNU General Public License
# along with this program; if not, write to the Free Software
# Foundation, Inc., 51 Franklin Street, Fifth Floor, Boston, MA 02110-1301, USA.
#
# http://github.com/TBD
#
from MDOTools.ValidGrad.FDValidGrad import FDValidGrad
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)
#
# You should have received a copy of the GNU General Public License
# along with this program; if not, write to the Free Software
# Foundation, Inc., 51 Franklin Street, Fifth Floor, Boston, MA 02110-1301, USA.
#
# http://github.com/TBD
#
from DLLM.DLLMGeom.wing_param import 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)
# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
# GNU General Public License for more details.
#
# You should have received a copy of the GNU General Public License
# along with this program; if not, write to the Free Software
# Foundation, Inc., 51 Franklin Street, Fifth Floor, Boston, MA 02110-1301, USA.
#
# http://github.com/TBD
#
# 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
