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 = 'aerodynamics_markup'
self.geometry = Data()
self.settings = Data()
self.process = Process()
self.process.initialize = Process()
self.process.compute = Process()
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 = 'AVL_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
# Build the evaluation process
compute = self.process.compute
compute.lift = Process()
# Run AVL to determine lift
compute.lift.inviscid = AVL_Inviscid()
compute.lift.total = Common.Lift.aircraft_total
# Do a traditional drag buildup
compute.drag = Process()
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.propulsors = Process_Geometry('propulsors')
compute.drag.parasite.propulsors.propulsor = Common.Drag.parasite_drag_propulsor
compute.drag.parasite.pylons = Common.Drag.parasite_drag_pylon
compute.drag.parasite.total = Common.Drag.parasite_total
compute.drag.induced = Common.Drag.induced_drag_aircraft
compute.drag.compressibility = Process()
compute.drag.compressibility.wings = Process_Geometry('wings')
compute.drag.compressibility.wings.wing = Common.Drag.compressibility_drag_wing
compute.drag.compressibility.total = Common.Drag.compressibility_drag_wing_total
compute.drag.miscellaneous = Common.Drag.miscellaneous_drag_aircraft_ESDU
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
class Markup(Aerodynamics):
""" SUAVE.Analyses.Aerodynamics.Markup()
"""
def __defaults__(self):
self.tag = 'aerodynamics_markup'
self.geometry = Data()
self.settings = Data()
self.process = Process()
self.process.initialize = Process()
self.process.compute = Process()
def evaluate(self, state):
settings = self.settings
geometry = self.geometry
results = self.process.compute(state, settings, geometry)
return results
def initialize(self):
self.process.initialize(self)
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 = 'aerodynamics_markup'
self.geometry = Data()
self.settings.maximum_lift_coefficient_factor = 1.0
self.settings.lift_to_drag_adjustment = 0. # (.1 is a 10% increase in L/D over base analysis)
# this is applied directly to the final drag value
self.process = Process()
self.process.initialize = Process()
self.process.compute = Process()
class Markup(Aerodynamics):
""" SUAVE.Analyses.Aerodynamics.Markup()
"""
def __defaults__(self):
self.tag = 'aerodynamics_markup'
self.geometry = Data()
self.settings = Data()
self.process = Process()
self.process.initialize = Process()
self.process.compute = Process()
def evaluate(self,state):
settings = self.settings
geometry = self.geometry
results = self.process.compute(state,settings,geometry)
return results
def initialize(self):
self.process.initialize(self)
def __defaults__(self):
# --------------------------------------------------------------
# State
# --------------------------------------------------------------
# conditions
self.state.conditions.update(Conditions.Basic())
# --------------------------------------------------------------
# The Solving Process
# --------------------------------------------------------------
# --------------------------------------------------------------
# Initialize - before iteration
# --------------------------------------------------------------
initialize = self.process.initialize
initialize.clear()
initialize.expand_state = Methods.expand_state
initialize.differentials = Methods.Common.Numerics.initialize_differentials_dimensionless
initialize.conditions = None
# --------------------------------------------------------------
# Converge - starts iteration
# --------------------------------------------------------------
converge = self.process.converge
converge.clear()
converge.converge_root = Methods.converge_root
# --------------------------------------------------------------
# Iterate - this is iterated
# --------------------------------------------------------------
iterate = self.process.iterate
iterate.clear()
# Update Initials
iterate.initials = Process()
iterate.initials.time = Methods.Common.Frames.initialize_time
# Unpack Unknowns
iterate.unpack_unknowns = None
# Update Conditions
iterate.conditions = Process()
iterate.conditions.differentials = Methods.Common.Numerics.update_differentials_time
# Solve Residuals
iterate.residuals = Process()
# --------------------------------------------------------------
# Finalize - after iteration
# --------------------------------------------------------------
finalize = self.process.finalize
finalize.clear()
finalize.post_process = Process()
return
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 = 'AERODAS Model'
settings = self.settings
settings.section_zero_lift_angle_of_attack = 0.0 * Units.deg
settings.section_minimum_drag_coefficient_angle_of_attack = 0.0 * Units.deg
settings.section_lift_curve_slope = 2.0 * np.pi
# build the evaluation process
compute = self.process.compute
compute.setup_data = Methods.AERODAS_setup.setup_data
# Get all of the coefficients for AERODAS wings
compute.wings_coefficients = Process()
compute.wings_coefficients = Process_Geometry('wings')
compute.wings_coefficients.section_properties = Methods.section_properties.section_properties
compute.wings_coefficients.finite_aspect_ratio = Methods.finite_aspect_ratio.finite_aspect_ratio
compute.wings_coefficients.pre_stall = Methods.pre_stall_coefficients.pre_stall_coefficients
compute.wings_coefficients.post_stall = Methods.post_stall_coefficients.post_stall_coefficients
# Fuselage drag?
# do a plate build up with angles
# Miscellaneous drag?
# Compressibility corrections?
compute.lift_drag_total = Methods.AERODAS_setup.lift_drag_total
compute.lift = Process()
compute.lift.total = Common.Lift.aircraft_total
compute.drag = Process()
compute.drag.total = Methods.AERODAS_setup.drag_total
def initialize(self):
super(AERODAS, self).initialize()
self.process.compute.lift.inviscid_wings.geometry = self.geometry
self.process.compute.lift.inviscid_wings.initialize()
finalize = initialize
def __defaults__(self):
self.tag = 'aerodynamics_markup'
self.geometry = Data()
self.settings = Data()
self.process = Process()
self.process.initialize = Process()
self.process.compute = Process()
class Container(Segment):
def __defaults__(self):
self.segments = Process()
self.state = State.Container()
def append_segment(self, segment):
""" Add a SubSegment """
self.segments.append(segment)
return
class Container(Segment):
""" A container for the segment
Assumptions:
None
Source:
None
"""
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
self.segments = Process()
self.state = State.Container()
def append_segment(self,segment):
""" Add a SubSegment
Assumptions:
None
Source:
N/A
Inputs:
segment [Segment()]
Outputs:
None
Properties Used:
None
"""
self.segments.append(segment)
return
class Container(Segment):
def __defaults__(self):
self.segments = Process()
self.state = State.Container()
def append_segment(self,segment):
""" Add a SubSegment """
self.segments.append(segment)
return
def __defaults__(self):
self.tag = 'SU2_Euler_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
settings.vsp_mesh_growth_limiting_flag = False
# Build the evaluation process
compute = self.process.compute
compute.lift = Process()
# Run SU2 to determine lift
compute.lift.inviscid = SU2_inviscid()
compute.lift.total = SUAVE.Methods.Aerodynamics.AERODAS.AERODAS_setup.lift_total
# Do a traditional drag buildup
compute.drag = Process()
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
compute.drag.parasite.total = Methods.Drag.parasite_total
compute.drag.induced = Methods.Drag.induced_drag_aircraft
compute.drag.compressibility = Process()
compute.drag.compressibility.wings = Process_Geometry('wings')
compute.drag.compressibility.wings.wing = Methods.Drag.compressibility_drag_wing
compute.drag.compressibility.total = Methods.Drag.compressibility_drag_wing_total
compute.drag.miscellaneous = Methods.Drag.miscellaneous_drag_aircraft_ESDU
compute.drag.untrimmed = SUAVE.Methods.Aerodynamics.SU2_Euler.untrimmed
compute.drag.trim = Methods.Drag.trim
compute.drag.spoiler = 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 = 'aerodynamics_markup'
self.geometry = Data()
self.settings = Data()
self.process = Process()
self.process.initialize = Process()
self.process.compute = Process()
def evaluate(self,state,settings,geometry):
"""Evaluates preset processes for each component.
Assumptions:
None
Source:
N/A
Inputs:
state (passed to an evaluation function)
setting (passed to an evaluation function)
geometry (used to get keys and passed to an evaluation function)
Outputs:
None
Properties Used:
self.geometry_key <string>
"""
geometry_items = geometry.deep_get(self.geometry_key)
results = Data()
for key, this_geometry in geometry_items.items():
result = Process.evaluate(self,state,settings,this_geometry)
results[key] = result
return results
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 = 'aerodynamics_markup'
self.geometry = Data()
self.settings.lift_to_drag_adjustment = 0. # (.1 is a 10% increase in L/D over base analysis)
# this is applied directly to the final drag value
self.process = Process()
self.process.initialize = Process()
self.process.compute = Process()
def evaluate(self, state, settings, geometry):
"""Evaluates preset processes for each component.
Assumptions:
None
Source:
N/A
Inputs:
state (passed to an evaluation function)
setting (passed to an evaluation function)
geometry (used to get keys and passed to an evaluation function)
Outputs:
None
Properties Used:
self.geometry_key <string>
"""
geometry_items = geometry.deep_get(self.geometry_key)
results = Results()
for key, this_geometry in geometry_items.items():
result = Process.evaluate(self, state, settings, this_geometry)
results[key] = result
return results
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
self.vehicle_configurations = SUAVE.Components.Configs.Config.Container()
self.analyses = SUAVE.Analyses.Analysis.Container()
self.missions = None
self.procedure = Process()
self.results = Data()
self.summary = Data()
self.optimization_problem = None
self.fidelity_level = 1
self.last_inputs = None
self.last_fidelity = None
self.evaluation_count = 0
self.force_evaluate = False
def __defaults__(self):
self.tag = 'Fidelity_Zero_Supersonic'
# correction factors
settings = self.settings
settings.fuselage_lift_correction = 1.14
settings.trim_drag_correction_factor = 1.02
settings.wing_parasite_drag_form_factor = 1.1
settings.fuselage_parasite_drag_form_factor = 2.3
settings.aircraft_span_efficiency_factor = 0.78
settings.viscous_lift_dependent_drag_factor = 0.38
settings.drag_coefficient_increment = 0.0000
settings.oswald_efficiency_factor = None
settings.maximum_lift_coefficient = np.inf
# vortex lattice configurations
settings.number_panels_spanwise = 5
settings.number_panels_chordwise = 1
# build the evaluation process
compute = self.process.compute
compute.lift = Process()
compute.lift.inviscid_wings = Vortex_Lattice()
compute.lift.vortex = Methods.Lift.vortex_lift # SZ
compute.lift.compressible_wings = Methods.Lift.wing_compressibility # SZ
compute.lift.fuselage = Methods.Lift.fuselage_correction # difference in results storage
compute.lift.total = Methods.Lift.aircraft_total # no difference
compute.drag = Process()
compute.drag.compressibility = Process()
compute.drag.compressibility.total = Methods.Drag.compressibility_drag_total # SZ
compute.drag.parasite = Process()
compute.drag.parasite.wings = Process_Geometry('wings')
compute.drag.parasite.wings.wing = Methods.Drag.parasite_drag_wing # SZ
compute.drag.parasite.fuselages = Process_Geometry('fuselages')
compute.drag.parasite.fuselages.fuselage = Methods.Drag.parasite_drag_fuselage # SZ
compute.drag.parasite.propulsors = Process_Geometry('propulsors')
compute.drag.parasite.propulsors.propulsor = Methods.Drag.parasite_drag_propulsor # SZ
#compute.drag.parasite.pylons = Methods.Drag.parasite_drag_pylon
compute.drag.parasite.total = Methods.Drag.parasite_total # SZ
compute.drag.induced = Methods.Drag.induced_drag_aircraft # SZ
compute.drag.miscellaneous = Methods.Drag.miscellaneous_drag_aircraft # different type used in FZ
compute.drag.untrimmed = Methods.Drag.untrimmed # SZ can be changed to match
compute.drag.trim = Methods.Drag.trim # SZ can be chanaged to match
compute.drag.total = Methods.Drag.total_aircraft # SZ
def __defaults__(self):
self.settings = Settings()
self.state = State()
self.analyses = Analysis.Container()
self.process = Process()
self.process.initialize = Process()
self.process.converge = Process()
self.process.iterate = Process()
self.process.iterate.unknowns = Process()
self.process.iterate.initials = Process()
self.process.iterate.conditions = Process()
self.process.iterate.residuals = Process()
self.process.finalize = Process()
return
def __defaults__(self):
self.vehicle_configurations = SUAVE.Components.Configs.Config.Container()
self.analyses = SUAVE.Analyses.Analysis.Container()
self.missions = None
self.procedure = Process()
self.results = SUAVE.Analyses.Results()
self.summary = Data()
self.optimization_problem = None
self.last_inputs = None
self.evaluation_count = 0
def __defaults__(self):
self.tag = 'aerodynamics_markup'
self.geometry = Data()
self.settings = Data()
self.process = Process()
self.process.initialize = Process()
self.process.compute = Process()
def evaluate(self, state, settings, geometry):
geometry_items = geometry.deep_get(self.geometry_key)
results = Results()
for key, this_geometry in geometry_items.items():
result = Process.evaluate(self, state, settings, this_geometry)
results[key] = result
return results
def __defaults__(self):
self.settings = Settings()
self.state = State()
self.analyses = Analysis.Container()
self.process = Process()
self.process.initialize = Process()
self.process.converge = Process()
self.process.iterate = Process()
self.process.finalize = Process()
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
self.segments = Process()
self.state = State.Container()
def __defaults__(self):
self.tag = 'AERODAS Model'
settings = self.settings
settings.section_zero_lift_angle_of_attack = 0.0 * Units.deg
settings.section_lift_curve_slope = 2.0 * np.pi
# build the evaluation process
compute = self.process.compute
compute.setup_data = Methods.AERODAS_setup.setup_data
# Get all of the coefficients for AERODAS wings
compute.wings_coefficients = Process()
compute.wings_coefficients = Process_Geometry('wings')
compute.wings_coefficients.section_properties = Methods.section_properties.section_properties
compute.wings_coefficients.finite_aspect_ratio = Methods.finite_aspect_ratio.finite_aspect_ratio
compute.wings_coefficients.pre_stall = Methods.pre_stall_coefficients.pre_stall_coefficients
compute.wings_coefficients.post_stall = Methods.post_stall_coefficients.post_stall_coefficients
# Fuselage drag?
# do a plate build up with angles
# Miscellaneous drag?
# Compressibility corrections?
compute.lift_drag_total = Methods.AERODAS_setup.lift_drag_total
compute.lift = Process()
compute.lift.total = Methods.AERODAS_setup.lift_total
compute.drag = Process()
compute.drag.total = Methods.AERODAS_setup.drag_total
def initialize(self):
self.process.compute.lift.inviscid_wings.geometry = self.geometry
self.process.compute.lift.inviscid_wings.initialize()
finalize = initialize
def evaluate(self,state,settings,geometry):
geometry_items = geometry.deep_get(self.geometry_key)
results = Results()
for key, this_geometry in geometry_items.items():
result = Process.evaluate(self,state,settings,this_geometry)
results[key] = result
return results
class Segment(Analysis):
def __defaults__(self):
self.settings = Settings()
self.state = State()
self.analyses = Analysis.Container()
self.process = Process()
self.process.initialize = Process()
self.process.converge = Process()
self.process.iterate = Process()
self.process.iterate.unknowns = Process()
self.process.iterate.initials = Process()
self.process.iterate.conditions = Process()
self.process.iterate.residuals = Process()
self.process.finalize = Process()
self.process.finalize.post_process = Process()
return
def initialize(self, state):
self.process.initialize(self, state)
return
def converge(self, state):
self.process.converge(self, state)
def iterate(self, state):
self.process.iterate(self, state)
return
def finalize(self, state):
self.process.finalize(self, state)
return
def compile(self):
return
def evaluate(self, state=None):
if state is None:
state = self.state
self.process(self, state)
return state
class Segment(Analysis):
def __defaults__(self):
self.settings = Settings()
self.state = State()
self.analyses = Analysis.Container()
self.process = Process()
self.process.initialize = Process()
self.process.converge = Process()
self.process.iterate = Process()
self.process.iterate.initials = Process()
self.process.iterate.conditions = Process()
self.process.finalize = Process()
def initialize(self,state):
self.process.initialize(self,state)
return
def converge(self,state):
self.process.converge(self,state)
def iterate(self,state):
self.process.iterate(self,state)
return
def finalize(self,state):
self.process.finalize(self,state)
return
def compile(self):
return
def evaluate(self,state=None):
if state is None:
state = deepcopy(self.state)
self.process(self,state)
return state
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
self.segments = Process()
self.state = State.Container()
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
self.settings = Settings()
self.state = State()
self.analyses = Analysis.Container()
self.process = Process()
self.process.initialize = Process()
self.process.converge = Process()
self.process.iterate = Process()
self.process.iterate.unknowns = Process()
self.process.iterate.initials = Process()
self.process.iterate.conditions = Process()
self.process.iterate.residuals = Process()
self.process.finalize = Process()
self.process.finalize.post_process = Process()
self.conditions = self.state.conditions
return
class Markup(Aerodynamics):
"""This is an intermediate class for aerodynamic analyses.
Assumptions:
None
Source:
N/A
"""
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 = 'aerodynamics_markup'
self.geometry = Data()
self.settings = Data()
self.process = Process()
self.process.initialize = Process()
self.process.compute = Process()
def evaluate(self,state):
"""The default evaluate function.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
results <SUAVE data class>
Properties Used:
self.settings
self.geometry
"""
settings = self.settings
geometry = self.geometry
results = self.process.compute(state,settings,geometry)
return results
def initialize(self):
"""The default finalize function. Calls the initialize process.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
self.process.initialize(self)
class Segment(Analysis):
""" The first basic piece of a mission which each segment will expand upon
Assumptions:
There's a detailed process flow outline in defaults. A mission must be solved in that order.
Source:
None
"""
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
self.settings = Settings()
self.state = State()
self.analyses = Analysis.Container()
self.process = Process()
self.process.initialize = Process()
self.process.converge = Process()
self.process.iterate = Process()
self.process.iterate.unknowns = Process()
self.process.iterate.initials = Process()
self.process.iterate.conditions = Process()
self.process.iterate.residuals = Process()
self.process.finalize = Process()
self.process.finalize.post_process = Process()
self.conditions = self.state.conditions
return
def initialize(self):
""" This executes the initialize process
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
None
Properties Used:
None
"""
state = self.state
self.process.initialize(self)
return
def converge(self,state):
""" This executes the converge process
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
None
Properties Used:
None
"""
self.process.converge(self,state)
def iterate(self):
""" This executes the iterate process
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
None
Properties Used:
None
"""
self.process.iterate(self)
return
def finalize(self):
""" This executes the finalize process
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
None
Properties Used:
None
"""
self.process.finalize(self)
return
def compile(self):
""" This does nothing
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
None
Properties Used:
None
"""
return
def evaluate(self,state=None):
""" This executes the entire process
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
State [Data()]
Properties Used:
None
"""
if state is None:
state = self.state
self.process(self)
return self
def merged(self):
""" Combines the states of multiple segments
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
state_out [State()]
Properties Used:
None
"""
state_out = State()
for i,(tag,sub_seg) in enumerate(self.segments.items()):
sub_state = sub_seg.state
for key in ['unknowns','conditions','residuals']:
if i == 0:
state_out[key].update(sub_state[key])
else:
state_out[key] = state_out[key].do_recursive(append_array,sub_state[key])
return state_out
class Markup(Aerodynamics):
"""This is an intermediate class for aerodynamic analyses.
Assumptions:
None
Source:
N/A
"""
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 = 'aerodynamics_markup'
self.geometry = Data()
self.settings.lift_to_drag_adjustment = 0. # (.1 is a 10% increase in L/D over base analysis)
# this is applied directly to the final drag value
self.process = Process()
self.process.initialize = Process()
self.process.compute = Process()
def evaluate(self,state):
"""The default evaluate function.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
results <SUAVE data class>
Properties Used:
self.settings
self.geometry
"""
settings = self.settings
geometry = self.geometry
results = self.process.compute(state,settings,geometry)
return results
def initialize(self):
"""The default finalize function. Calls the initialize process.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
self.process.initialize(self)
def __defaults__(self):
self.tag = 'fidelity_zero_markup'
## available from Markup
#self.geometry = Data()
#self.settings = Data()
#self.process = Process()
#self.process.initialize = Process()
#self.process.compute = Process()
# correction factors
settings = self.settings
settings.fuselage_lift_correction = 1.14
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
# vortex lattice configurations
settings.number_panels_spanwise = 5
settings.number_panels_chordwise = 1
# build the evaluation process
compute = self.process.compute
# these methods have interface as
# results = function(state,settings,geometry)
# results are optional
# first stub out empty functions
# then implement methods
# then we'll figure out how to connect to a mission
compute.lift = Process()
compute.lift.inviscid_wings = Vortex_Lattice()
compute.lift.vortex = SUAVE.Methods.skip
compute.lift.compressible_wings = Methods.Lift.wing_compressibility_correction
compute.lift.fuselage = Methods.Lift.fuselage_correction
compute.lift.total = Methods.Lift.aircraft_total
compute.drag = Process()
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
compute.drag.parasite.total = Methods.Drag.parasite_total
compute.drag.induced = Methods.Drag.induced_drag_aircraft
compute.drag.compressibility = Process()
compute.drag.compressibility.wings = Process_Geometry('wings')
compute.drag.compressibility.wings.wing = Methods.Drag.compressibility_drag_wing
compute.drag.compressibility.total = Methods.Drag.compressibility_drag_wing_total
compute.drag.miscellaneous = Methods.Drag.miscellaneous_drag_aircraft_ESDU
compute.drag.untrimmed = Methods.Drag.untrimmed
compute.drag.trim = Methods.Drag.trim
compute.drag.spoiler = Methods.Drag.spoiler_drag
compute.drag.total = Methods.Drag.total_aircraft
def __defaults__(self):
""" This sets the default solver flow. Anything in here can be modified after initializing a segment.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
# --------------------------------------------------------------
# User inputs
# --------------------------------------------------------------
self.altitude_start = None # Optional
self.altitude_end = 10. * Units.km
# --------------------------------------------------------------
# State
# --------------------------------------------------------------
# conditions
self.state.conditions.update(Conditions.Aerodynamics())
# initials and unknowns
ones_row = self.state.ones_row
self.state.unknowns.throttle = ones_row(1) * 0.5
self.state.unknowns.body_angle = ones_row(1) * 0.0
self.state.residuals.forces = ones_row(2) * 0.0
# --------------------------------------------------------------
# The Solving Process
# --------------------------------------------------------------
# --------------------------------------------------------------
# Initialize - before iteration
# --------------------------------------------------------------
initialize = self.process.initialize
initialize.expand_state = Methods.expand_state
initialize.differentials = Methods.Common.Numerics.initialize_differentials_dimensionless
initialize.conditions = None
initialize.differentials_altitude = Methods.Climb.Common.update_differentials_altitude
# --------------------------------------------------------------
# Converge - starts iteration
# --------------------------------------------------------------
converge = self.process.converge
converge.converge_root = Methods.converge_root
# --------------------------------------------------------------
# Iterate - this is iterated
# --------------------------------------------------------------
iterate = self.process.iterate
# Update Initials
iterate.initials = Process()
iterate.initials.time = Methods.Common.Frames.initialize_time
iterate.initials.weights = Methods.Common.Weights.initialize_weights
iterate.initials.inertial_position = Methods.Common.Frames.initialize_inertial_position
iterate.initials.planet_position = Methods.Common.Frames.initialize_planet_position
# Unpack Unknowns
iterate.unknowns = Process()
iterate.unknowns.mission = Methods.Climb.Common.unpack_unknowns
# Update Conditions
iterate.conditions = Process()
iterate.conditions.differentials = Methods.Common.Numerics.update_differentials_time
iterate.conditions.acceleration = Methods.Common.Frames.update_acceleration
iterate.conditions.altitude = Methods.Common.Aerodynamics.update_altitude
iterate.conditions.atmosphere = Methods.Common.Aerodynamics.update_atmosphere
iterate.conditions.gravity = Methods.Common.Weights.update_gravity
iterate.conditions.freestream = Methods.Common.Aerodynamics.update_freestream
iterate.conditions.orientations = Methods.Common.Frames.update_orientations
iterate.conditions.aerodynamics = Methods.Common.Aerodynamics.update_aerodynamics
iterate.conditions.stability = Methods.Common.Aerodynamics.update_stability
iterate.conditions.propulsion = Methods.Common.Energy.update_thrust
iterate.conditions.weights = Methods.Common.Weights.update_weights
iterate.conditions.forces = Methods.Common.Frames.update_forces
iterate.conditions.planet_position = Methods.Common.Frames.update_planet_position
# Solve Residuals
iterate.residuals = Process()
iterate.residuals.total_forces = Methods.Climb.Common.residual_total_forces
# --------------------------------------------------------------
# Finalize - after iteration
# --------------------------------------------------------------
finalize = self.process.finalize
# Post Processing
finalize.post_process = Process()
finalize.post_process.inertial_position = Methods.Common.Frames.integrate_inertial_horizontal_position
finalize.post_process.stability = Methods.Common.Aerodynamics.update_stability
return
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 = 'Fidelity_Zero_Supersonic'
# correction factors
settings = self.settings
settings.fuselage_lift_correction = 1.14
settings.trim_drag_correction_factor = 1.02
settings.wing_parasite_drag_form_factor = 1.1
settings.fuselage_parasite_drag_form_factor = 2.3
settings.aircraft_span_efficiency_factor = 0.78
settings.viscous_lift_dependent_drag_factor = 0.38
settings.drag_coefficient_increment = 0.0000
settings.spoiler_drag_increment = 0.00
settings.oswald_efficiency_factor = None
settings.maximum_lift_coefficient = np.inf
# vortex lattice configurations
settings.number_panels_spanwise = 5
settings.number_panels_chordwise = 1
# build the evaluation process
compute = self.process.compute
compute.lift = Process()
compute.lift.inviscid_wings = Vortex_Lattice()
compute.lift.vortex = Methods.Lift.vortex_lift # SZ
compute.lift.compressible_wings = Methods.Lift.wing_compressibility # SZ
compute.lift.fuselage = Common.Lift.fuselage_correction
compute.lift.total = Common.Lift.aircraft_total
compute.drag = Process()
compute.drag.compressibility = Process()
compute.drag.compressibility.total = Methods.Drag.compressibility_drag_total # SZ
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.propulsors = Process_Geometry('propulsors')
compute.drag.parasite.propulsors.propulsor = Methods.Drag.parasite_drag_propulsor # SZ
#compute.drag.parasite.pylons = Methods.Drag.parasite_drag_pylon
compute.drag.parasite.total = Common.Drag.parasite_total
compute.drag.induced = Methods.Drag.induced_drag_aircraft # SZ
compute.drag.miscellaneous = Methods.Drag.miscellaneous_drag_aircraft # different type used in FZ
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 # SZ
def __defaults__(self):
""" This sets the default solver flow. Anything in here can be modified after initializing a segment.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
# --------------------------------------------------------------
# User inputs
# --------------------------------------------------------------
self.altitude = None
self.air_speed = 10. * Units['km/hr']
self.throttle = 1.
self.z_accel = 0. # note that down is positive
self.state.numerics.number_control_points = 1
# --------------------------------------------------------------
# State
# --------------------------------------------------------------
# conditions
self.state.conditions.update( Conditions.Aerodynamics() )
# initials and unknowns
self.state.unknowns.x_accel = np.array([[0.0]])
self.state.unknowns.body_angle = np.array([[0.5]])
self.state.residuals.forces = np.array([[0.0,0.0]])
# --------------------------------------------------------------
# The Solving Process
# --------------------------------------------------------------
# --------------------------------------------------------------
# Initialize - before iteration
# --------------------------------------------------------------
initialize = self.process.initialize
initialize.expand_state = skip
initialize.differentials = skip
initialize.conditions = Methods.Single_Point.Set_Speed_Set_Throttle.initialize_conditions
# --------------------------------------------------------------
# Converge - starts iteration
# --------------------------------------------------------------
converge = self.process.converge
converge.converge_root = Methods.converge_root
# --------------------------------------------------------------
# Iterate - this is iterated
# --------------------------------------------------------------
iterate = self.process.iterate
# Update Initials
iterate.initials = Process()
iterate.initials.time = Methods.Common.Frames.initialize_time
iterate.initials.weights = Methods.Common.Weights.initialize_weights
iterate.initials.inertial_position = Methods.Common.Frames.initialize_inertial_position
iterate.initials.planet_position = Methods.Common.Frames.initialize_planet_position
# Unpack Unknowns
iterate.unknowns = Process()
iterate.unknowns.mission = Methods.Single_Point.Set_Speed_Set_Throttle.unpack_unknowns
# Update Conditions
iterate.conditions = Process()
iterate.conditions.differentials = skip
iterate.conditions.altitude = Methods.Common.Aerodynamics.update_altitude
iterate.conditions.atmosphere = Methods.Common.Aerodynamics.update_atmosphere
iterate.conditions.gravity = Methods.Common.Weights.update_gravity
iterate.conditions.freestream = Methods.Common.Aerodynamics.update_freestream
iterate.conditions.orientations = Methods.Common.Frames.update_orientations
iterate.conditions.propulsion = Methods.Common.Energy.update_thrust
iterate.conditions.aerodynamics = Methods.Common.Aerodynamics.update_aerodynamics
iterate.conditions.stability = Methods.Common.Aerodynamics.update_stability
iterate.conditions.weights = Methods.Single_Point.Set_Speed_Set_Throttle.update_weights
iterate.conditions.forces = Methods.Common.Frames.update_forces
iterate.conditions.planet_position = skip
# Solve Residuals
iterate.residuals = Process()
iterate.residuals.total_forces = Methods.Climb.Common.residual_total_forces
# --------------------------------------------------------------
# Finalize - after iteration
# --------------------------------------------------------------
finalize = self.process.finalize
# Post Processing
finalize.post_process = Process()
finalize.post_process.inertial_position = skip
finalize.post_process.stability = Methods.Common.Aerodynamics.update_stability
return
class Markup(Aerodynamics):
"""This is an intermediate class for aerodynamic analyses.
Assumptions:
None
Source:
N/A
"""
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 = 'aerodynamics_markup'
self.geometry = Data()
self.settings = Data()
self.process = Process()
self.process.initialize = Process()
self.process.compute = Process()
def evaluate(self, state):
"""The default evaluate function.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
results <SUAVE data class>
Properties Used:
self.settings
self.geometry
"""
settings = self.settings
geometry = self.geometry
results = self.process.compute(state, settings, geometry)
return results
def initialize(self):
"""The default finalize function. Calls the initialize process.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
self.process.initialize(self)
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
self.settings = Settings()
self.state = State()
self.analyses = Analysis.Container()
self.process = Process()
self.process.initialize = Process()
self.process.converge = Process()
self.process.iterate = Process()
self.process.iterate.unknowns = Process()
self.process.iterate.initials = Process()
self.process.iterate.conditions = Process()
self.process.iterate.residuals = Process()
self.process.finalize = Process()
self.process.finalize.post_process = Process()
self.conditions = self.state.conditions
return
class Segment(Analysis):
""" The first basic piece of a mission which each segment will expand upon
Assumptions:
There's a detailed process flow outline in defaults. A mission must be solved in that order.
Source:
None
"""
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
self.settings = Settings()
self.state = State()
self.analyses = Analysis.Container()
self.process = Process()
self.process.initialize = Process()
self.process.converge = Process()
self.process.iterate = Process()
self.process.iterate.unknowns = Process()
self.process.iterate.initials = Process()
self.process.iterate.conditions = Process()
self.process.iterate.residuals = Process()
self.process.finalize = Process()
self.process.finalize.post_process = Process()
self.conditions = self.state.conditions
return
def initialize(self):
""" This executes the initialize process
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
None
Properties Used:
None
"""
state = self.state
self.process.initialize(self)
return
def converge(self, state):
""" This executes the converge process
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
None
Properties Used:
None
"""
self.process.converge(self, state)
def iterate(self):
""" This executes the iterate process
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
None
Properties Used:
None
"""
self.process.iterate(self)
return
def finalize(self):
""" This executes the finalize process
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
None
Properties Used:
None
"""
self.process.finalize(self)
return
def evaluate(self, state=None):
""" This executes the entire process
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
State [Data()]
Properties Used:
None
"""
if state is None:
state = self.state
self.process(self)
return self
def merged(self):
""" Combines the states of multiple segments
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
state_out [State()]
Properties Used:
None
"""
state_out = State()
for i, (tag, sub_seg) in enumerate(self.segments.items()):
sub_state = sub_seg.state
for key in ['unknowns', 'conditions', 'residuals']:
if i == 0:
state_out[key] = deepcopy(
sub_state[key]
) # Necessary deepcopy: otherwise the next step overwrites this state
else:
state_out[key].append_or_update(sub_state[key])
return state_out
class Segment(Analysis):
""" The first basic piece of a mission which each segment will expand upon
Assumptions:
There's a detailed process flow outline in defaults. A mission must be solved in that order.
Source:
None
"""
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
self.settings = Settings()
self.state = State()
self.analyses = Analysis.Container()
self.process = Process()
self.process.initialize = Process()
self.process.converge = Process()
self.process.iterate = Process()
self.process.iterate.unknowns = Process()
self.process.iterate.initials = Process()
self.process.iterate.conditions = Process()
self.process.iterate.residuals = Process()
self.process.finalize = Process()
self.process.finalize.post_process = Process()
return
def initialize(self,state):
""" This executes the initialize process
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
None
Properties Used:
None
"""
self.process.initialize(self,state)
return
def converge(self,state):
""" This executes the converge process
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
None
Properties Used:
None
"""
self.process.converge(self,state)
def iterate(self,state):
""" This executes the iterate process
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
None
Properties Used:
None
"""
self.process.iterate(self,state)
return
def finalize(self,state):
""" This executes the finalize process
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
None
Properties Used:
None
"""
self.process.finalize(self,state)
return
def compile(self):
""" This does nothing
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
None
Properties Used:
None
"""
return
def evaluate(self,state=None):
""" This executes the entire process
Assumptions:
None
Source:
N/A
Inputs:
State [Data()]
Outputs:
State [Data()]
Properties Used:
None
"""
if state is None:
state = self.state
self.process(self,state)
return state
def __defaults__(self):
""" This sets the default solver flow. Anything in here can be modified after initializing a segment.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
# --------------------------------------------------------------
# User inputs
# --------------------------------------------------------------
self.altitude_start = None
self.altitude_end = None
self.air_speed_start = None
self.air_speed_end = None
self.objective = None # This will be a key
self.minimize = True
self.CL_limit = 1.e20
self.seed_climb_rate = 100. * Units['feet/min']
self.algorithm = 'SLSQP'
# --------------------------------------------------------------
# State
# --------------------------------------------------------------
# conditions
self.state.conditions.update(Conditions.Aerodynamics())
# initials and unknowns
ones_row = self.state.ones_row
self.state.unknowns.throttle = ones_row(1) * 0.8
self.state.unknowns.body_angle = ones_row(1) * 5.0 * Units.degrees
self.state.unknowns.flight_path_angle = ones_row(
1) * 3.0 * Units.degrees
self.state.unknowns.velocity = ones_row(1) * 1.0
self.state.residuals.forces = ones_row(2) * 0.0
self.state.inputs_last = None
self.state.objective_value = 0.0
self.state.constraint_values = 0.0
# --------------------------------------------------------------
# The Solving Process
# --------------------------------------------------------------
# --------------------------------------------------------------
# Initialize - before iteration
# --------------------------------------------------------------
initialize = self.process.initialize
initialize.expand_state = Methods.expand_state
initialize.solved_mission = Methods.Climb.Optimized.solve_linear_speed_constant_rate
initialize.differentials = Methods.Common.Numerics.initialize_differentials_dimensionless
initialize.conditions = SUAVE.Methods.skip
# --------------------------------------------------------------
# Converge - starts iteration
# --------------------------------------------------------------
converge = self.process.converge
converge.converge_root = Methods.converge_opt
# --------------------------------------------------------------
# Iterate - this is iterated
# --------------------------------------------------------------
iterate = self.process.iterate
# Update Initials
iterate.initials = Process()
iterate.initials.time = Methods.Common.Frames.initialize_time
iterate.initials.weights = Methods.Common.Weights.initialize_weights
iterate.initials.inertial_position = Methods.Common.Frames.initialize_inertial_position
iterate.initials.planet_position = Methods.Common.Frames.initialize_planet_position
# Unpack Unknowns
iterate.unknowns = Process()
iterate.unknowns.mission = Methods.Climb.Optimized.unpack_unknowns
# Update Conditions
iterate.conditions = Process()
iterate.conditions.differentials = Methods.Climb.Optimized.update_differentials
iterate.conditions.acceleration = Methods.Common.Frames.update_acceleration
iterate.conditions.altitude = Methods.Common.Aerodynamics.update_altitude
iterate.conditions.atmosphere = Methods.Common.Aerodynamics.update_atmosphere
iterate.conditions.gravity = Methods.Common.Weights.update_gravity
iterate.conditions.freestream = Methods.Common.Aerodynamics.update_freestream
iterate.conditions.orientations = Methods.Common.Frames.update_orientations
iterate.conditions.aerodynamics = Methods.Common.Aerodynamics.update_aerodynamics
iterate.conditions.stability = Methods.Common.Aerodynamics.update_stability
iterate.conditions.propulsion = Methods.Common.Energy.update_thrust
iterate.conditions.weights = Methods.Common.Weights.update_weights
iterate.conditions.forces = Methods.Common.Frames.update_forces
iterate.conditions.planet_position = Methods.Common.Frames.update_planet_position
# Solve Residuals
iterate.residuals = Process()
iterate.residuals.total_forces = Methods.Climb.Common.residual_total_forces
# Set outputs
iterate.outputs = Process()
iterate.outputs.objective = Methods.Climb.Optimized.objective
iterate.outputs.constraints = Methods.Climb.Optimized.constraints
iterate.outputs.cache_inputs = Methods.Climb.Optimized.cache_inputs
# --------------------------------------------------------------
# Finalize - after iteration
# --------------------------------------------------------------
finalize = self.process.finalize
# Post Processing
finalize.post_process = Process()
finalize.post_process.inertial_position = Methods.Common.Frames.integrate_inertial_horizontal_position
finalize.post_process.stability = Methods.Common.Aerodynamics.update_stability
return
def __defaults__(self):
self.segments = Process()
self.state = State.Container()
def __defaults__(self):
self.segments = Process()
self.state = State.Container()
def __defaults__(self):
# --------------------------------------------------------------
# User inputs
# --------------------------------------------------------------
self.altitude_start = None # Optional
self.altitude_end = 10. * Units.km
self.throttle = 0.5
self.equivalent_air_speed = 100 * Units.kts
self.settings.root_finder = scipy.optimize.root
# --------------------------------------------------------------
# State
# --------------------------------------------------------------
# conditions
self.state.conditions.update(Conditions.Aerodynamics())
# initials and unknowns
ones_row = self.state.ones_row
self.state.unknowns.body_angle = ones_row(1) * 10.0 * Units.deg
self.state.unknowns.wind_angle = ones_row(1) * 0.8 * Units.deg
self.state.residuals.forces = ones_row(2) * 0.0
# --------------------------------------------------------------
# The Solving Process
# --------------------------------------------------------------
# --------------------------------------------------------------
# Initialize - before iteration
# --------------------------------------------------------------
initialize = self.process.initialize
initialize.clear()
initialize.expand_state = Methods.expand_state
initialize.differentials = Methods.Common.Numerics.initialize_differentials_dimensionless
initialize.conditions = Methods.Climb.Constant_Throttle_Constant_EAS.initialize_conditions
initialize.velocities = Methods.Climb.Constant_Throttle_Constant_EAS.update_velocity_vector_from_wind_angle
initialize.differentials_altitude = Methods.Climb.Constant_Throttle_Constant_EAS.update_differentials_time
# --------------------------------------------------------------
# Converge - starts iteration
# --------------------------------------------------------------
converge = self.process.converge
converge.clear()
converge.converge_root = Methods.converge_root
# --------------------------------------------------------------
# Iterate - this is iterated
# --------------------------------------------------------------
iterate = self.process.iterate
iterate.clear()
# Update Initials
iterate.initials = Process()
iterate.initials.time = Methods.Common.Frames.initialize_time
iterate.initials.weights = Methods.Common.Weights.initialize_weights
iterate.initials.inertial_position = Methods.Common.Frames.initialize_inertial_position
iterate.initials.planet_position = Methods.Common.Frames.initialize_planet_position
# Unpack Unknowns
iterate.unpack_unknowns = Methods.Climb.Constant_Throttle_Constant_EAS.unpack_body_angle
# Update Conditions
iterate.conditions = Process()
iterate.conditions.velocities = Methods.Climb.Constant_Throttle_Constant_EAS.update_velocity_vector_from_wind_angle
iterate.conditions.differentials_a = Methods.Climb.Constant_Throttle_Constant_EAS.update_differentials_time
iterate.conditions.acceleration = Methods.Climb.Constant_Throttle_Constant_EAS.update_acceleration
iterate.conditions.altitude = Methods.Common.Aerodynamics.update_altitude
iterate.conditions.atmosphere = Methods.Common.Aerodynamics.update_atmosphere
iterate.conditions.gravity = Methods.Common.Weights.update_gravity
iterate.conditions.freestream = Methods.Common.Aerodynamics.update_freestream
iterate.conditions.orientations = Methods.Common.Frames.update_orientations
iterate.conditions.aerodynamics = Methods.Common.Aerodynamics.update_aerodynamics
iterate.conditions.stability = Methods.Common.Aerodynamics.update_stability
iterate.conditions.propulsion = Methods.Common.Energy.update_thrust
iterate.conditions.weights = Methods.Climb.Constant_Throttle_Constant_EAS.update_weights
iterate.conditions.forces = Methods.Climb.Constant_Throttle_Constant_EAS.update_forces
iterate.conditions.planet_position = Methods.Common.Frames.update_planet_position
# Solve Residuals
iterate.residuals = Process()
iterate.residuals.total_forces = Methods.Climb.Constant_Throttle_Constant_EAS.residual_total_forces
# --------------------------------------------------------------
# Finalize - after iteration
# --------------------------------------------------------------
finalize = self.process.finalize
finalize.clear()
# Post Processing
finalize.post_process = Process()
finalize.post_process.inertial_position = Methods.Common.Frames.integrate_inertial_horizontal_position
finalize.post_process.stability = Methods.Common.Aerodynamics.update_stability
return
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.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 = 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.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 = Common.Drag.parasite_total
compute.drag.induced = Methods.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 = FZ_Methods.Drag.spoiler_drag
compute.drag.total = Common.Drag.total_aircraft