Python wing_param.Wing_param类代码示例

 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 __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)

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
    

#
# 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.))

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)
#.........这里部分代码省略.........

#
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

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()

 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)

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
#.........这里部分代码省略.........

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 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 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.)