def __defaults__(self):
self.tag = 'SU2_Euler_Super_markup'
# Correction factors
settings = self.settings
settings.trim_drag_correction_factor = 1.02
settings.wing_parasite_drag_form_factor = 1.1
settings.fuselage_parasite_drag_form_factor = 2.3
settings.oswald_efficiency_factor = None
settings.viscous_lift_dependent_drag_factor = 0.38
settings.drag_coefficient_increment = 0.0000
settings.spoiler_drag_increment = 0.00
settings.maximum_lift_coefficient = np.inf
settings.half_mesh_flag = True
settings.parallel = False
settings.processors = 1
settings.vsp_mesh_growth_ratio = 1.3
# Build the evaluation process
compute = self.process.compute
compute.lift = Process()
# Run SU2
compute.lift.inviscid = SU2_inviscid_Super()
compute.lift.total = SUAVE.Methods.Aerodynamics.AERODAS.AERODAS_setup.lift_total
# Do a traditional drag buildup
compute.drag = Process()
compute.drag.compressibility = Process()
compute.drag.compressibility.total = Methods.Drag.compressibility_drag_total
compute.drag.parasite = Process()
compute.drag.parasite.wings = Process_Geometry('wings')
compute.drag.parasite.wings.wing = Methods.Drag.parasite_drag_wing
compute.drag.parasite.fuselages = Process_Geometry('fuselages')
compute.drag.parasite.fuselages.fuselage = Methods.Drag.parasite_drag_fuselage
compute.drag.parasite.propulsors = Process_Geometry('propulsors')
compute.drag.parasite.propulsors.propulsor = Methods.Drag.parasite_drag_propulsor
#compute.drag.parasite.pylons = Methods.Drag.parasite_drag_pylon # currently unavailable for supersonic
compute.drag.parasite.total = Methods.Drag.parasite_total
compute.drag.induced = Methods.Drag.induced_drag_aircraft
compute.drag.miscellaneous = Methods.Drag.miscellaneous_drag_aircraft
compute.drag.untrimmed = SUAVE.Methods.Aerodynamics.SU2_Euler.untrimmed
compute.drag.trim = Methods.Drag.trim
compute.drag.spoiler = FZ_Methods.Drag.spoiler_drag
compute.drag.total = SUAVE.Methods.Aerodynamics.SU2_Euler.total_aircraft_drag
def __defaults__(self):
"""This sets the default values and methods for the analysis.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
self.tag = 'SU2_Euler_Super_markup'
# Correction factors
settings = self.settings
settings.trim_drag_correction_factor = 1.02
settings.wing_parasite_drag_form_factor = 1.1
settings.fuselage_parasite_drag_form_factor = 2.3
settings.oswald_efficiency_factor = None
settings.span_efficiency = None
settings.viscous_lift_dependent_drag_factor = 0.38
settings.drag_coefficient_increment = 0.0000
settings.spoiler_drag_increment = 0.00
settings.maximum_lift_coefficient = np.inf
settings.half_mesh_flag = True
settings.parallel = False
settings.processors = 1
settings.vsp_mesh_growth_ratio = 1.3
settings.vsp_mesh_growth_limiting_flag = False
settings.recalculate_total_wetted_area = False
# Build the evaluation process
compute = self.process.compute
compute.lift = Process()
# Run SU2
compute.lift.inviscid = SU2_inviscid_Super()
compute.lift.total = Common.Lift.aircraft_total
# Do a traditional drag buildup
compute.drag = Process()
compute.drag.compressibility = Process()
compute.drag.compressibility.total = Methods.Drag.compressibility_drag_total
compute.drag.parasite = Process()
compute.drag.parasite.wings = Process_Geometry('wings')
compute.drag.parasite.wings.wing = Common.Drag.parasite_drag_wing
compute.drag.parasite.fuselages = Process_Geometry('fuselages')
compute.drag.parasite.fuselages.fuselage = Common.Drag.parasite_drag_fuselage
compute.drag.parasite.nacelles = Process_Geometry('nacelles')
compute.drag.parasite.nacelles.nacelle = Methods.Drag.parasite_drag_nacelle
#compute.drag.parasite.pylons = Methods.Drag.parasite_drag_pylon # currently unavailable for supersonic
compute.drag.parasite.total = Common.Drag.parasite_total
compute.drag.induced = Common.Drag.induced_drag_aircraft
compute.drag.miscellaneous = Methods.Drag.miscellaneous_drag_aircraft
compute.drag.untrimmed = Common.Drag.untrimmed
compute.drag.trim = Common.Drag.trim
compute.drag.spoiler = Common.Drag.spoiler_drag
compute.drag.total = Common.Drag.total_aircraft