Esempio n. 1
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 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)
Esempio n. 2
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 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
Esempio n. 3
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 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)
Esempio n. 4
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 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)
Esempio n. 5
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 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)
Esempio n. 6
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 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
Esempio n. 7
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 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)
Esempio n. 8
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 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)
Esempio n. 9
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    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
Esempio n. 10
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 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)
Esempio n. 11
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 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)
Esempio n. 12
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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
Esempio n. 13
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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

#list_file = ['SimpleRect_3.00E-01.dat','SimpleRect_6.00E-01.dat','SimpleRect_8.00E-01.dat']
list_file = ['Elliptic_2.00E-01.dat']
Esempio n. 14
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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)]