Python OperatingCondition.set_Mach方法代码示例

# 需要导入模块: from MDOTools.OC.operating_condition import OperatingCondition [as 别名]
# 或者: from MDOTools.OC.operating_condition.OperatingCondition import set_Mach [as 别名]
 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

# 需要导入模块: from MDOTools.OC.operating_condition import OperatingCondition [as 别名]
# 或者: from MDOTools.OC.operating_condition.OperatingCondition import set_Mach [as 别名]
 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

# 需要导入模块: from MDOTools.OC.operating_condition import OperatingCondition [as 别名]
# 或者: from MDOTools.OC.operating_condition.OperatingCondition import set_Mach [as 别名]
 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

# 需要导入模块: from MDOTools.OC.operating_condition import OperatingCondition [as 别名]
# 或者: from MDOTools.OC.operating_condition.OperatingCondition import set_Mach [as 别名]
# 
#  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)

# 需要导入模块: from MDOTools.OC.operating_condition import OperatingCondition [as 别名]
# 或者: from MDOTools.OC.operating_condition.OperatingCondition import set_Mach [as 别名]
# 
#  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)

# 需要导入模块: from MDOTools.OC.operating_condition import OperatingCondition [as 别名]
# 或者: from MDOTools.OC.operating_condition.OperatingCondition import set_Mach [as 别名]
        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')

# 需要导入模块: from MDOTools.OC.operating_condition import OperatingCondition [as 别名]
# 或者: from MDOTools.OC.operating_condition.OperatingCondition import set_Mach [as 别名]
#  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

# 需要导入模块: from MDOTools.OC.operating_condition import OperatingCondition [as 别名]
# 或者: from MDOTools.OC.operating_condition.OperatingCondition import set_Mach [as 别名]

#.........这里部分代码省略.........
        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)]

# 需要导入模块: from MDOTools.OC.operating_condition import OperatingCondition [as 别名]
# 或者: from MDOTools.OC.operating_condition.OperatingCondition import set_Mach [as 别名]
#  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

# 需要导入模块: from MDOTools.OC.operating_condition import OperatingCondition [as 别名]
# 或者: from MDOTools.OC.operating_condition.OperatingCondition import set_Mach [as 别名]
#  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)

# 需要导入模块: from MDOTools.OC.operating_condition import OperatingCondition [as 别名]
# 或者: from MDOTools.OC.operating_condition.OperatingCondition import set_Mach [as 别名]
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)