def call_SU2(conditions, settings, geometry):
""" calculate total vehicle lift coefficient with SU2
"""
half_mesh_flag = settings.half_mesh_flag
tag = geometry.tag
parallel = settings.parallel
processors = settings.processors
iters = settings.maximum_iterations
SU2_settings = Data()
if half_mesh_flag == False:
SU2_settings.reference_area = geometry.reference_area
else:
SU2_settings.reference_area = geometry.reference_area / 2.
SU2_settings.mach_number = conditions.aerodynamics.mach
SU2_settings.angle_of_attack = conditions.aerodynamics.angle_of_attack / Units.deg
SU2_settings.maximum_iterations = iters
# Build SU2 configuration file
write_SU2_cfg(tag, SU2_settings)
# Run SU2
CL, CD = call_SU2_CFD(tag, parallel, processors)
return CL, CD
def call_SU2(conditions,settings,geometry):
"""Calculates lift and drag using SU2
Assumptions:
None
Source:
N/A
Inputs:
conditions.
mach_number [-]
angle_of_attack [radians]
settings.
half_mesh_flag <boolean> Determines if a symmetry plane is used
parallel <boolean>
processors [-]
maximum_iterations [-]
geometry.
tag
reference_area [m^2]
Outputs:
CL [-]
CD [-]
Properties Used:
N/A
"""
half_mesh_flag = settings.half_mesh_flag
tag = geometry.tag
parallel = settings.parallel
processors = settings.processors
iters = settings.maximum_iterations
SU2_settings = Data()
if half_mesh_flag == False:
SU2_settings.reference_area = geometry.reference_area
else:
SU2_settings.reference_area = geometry.reference_area/2.
SU2_settings.mach_number = conditions.aerodynamics.mach
SU2_settings.angle_of_attack = conditions.aerodynamics.angle_of_attack / Units.deg
SU2_settings.maximum_iterations = iters
# Build SU2 configuration file
write_SU2_cfg(tag, SU2_settings)
# Run SU2
CL, CD = call_SU2_CFD(tag,parallel,processors)
return CL, CD
def call_SU2(conditions,settings,geometry):
"""Calculates lift and drag using SU2
Assumptions:
None
Source:
N/A
Inputs:
conditions.
mach_number [-]
angle_of_attack [radians]
settings.
half_mesh_flag <boolean> Determines if a symmetry plane is used
parallel <boolean>
processors [-]
maximum_iterations [-]
geometry.
tag
reference_area [m^2]
Outputs:
CL [-]
CD [-]
Properties Used:
N/A
"""
half_mesh_flag = settings.half_mesh_flag
tag = geometry.tag
parallel = settings.parallel
processors = settings.processors
iters = settings.maximum_iterations
SU2_settings = Data()
if half_mesh_flag == False:
SU2_settings.reference_area = geometry.reference_area
else:
SU2_settings.reference_area = geometry.reference_area/2.
SU2_settings.mach_number = conditions.aerodynamics.mach
SU2_settings.angle_of_attack = conditions.aerodynamics.angle_of_attack / Units.deg
SU2_settings.maximum_iterations = iters
# Build SU2 configuration file
write_SU2_cfg(tag, SU2_settings)
# Run SU2
CL, CD = call_SU2_CFD(tag,parallel,processors)
return CL, CD