Source code for RCAIDE.Library.Methods.Aerodynamics.Athena_Vortex_Lattice.AVL_Objects.Run_Case
# RCAIDE/Library/Methods/Aerodynamics/Athena_Vortex_Lattice/AVL_Objects/Run_Case.py
#
# Created: Oct 2024, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
from RCAIDE.Framework.Core import Data , DataOrdered
# ----------------------------------------------------------------------------------------------------------------------
# Run_Case
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Run_Case(Data):
""" This data class defines the parameters for the analysis cases
including angle of attack and mach number
Assumptions:
None
Source:
None
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
def __defaults__(self):
"""Defines the data structure and defaults of aerodynamics coefficients,
body axis derivatives and stability axis derivatives
Assumptions:
None
Source:
None
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
self.index = 0
self.tag = 'case'
self.mass = 0.0
self.conditions = Data()
self.stability_and_control = Data()
self.stability_and_control.control_surface_names = None
self.stability_and_control.control_surface_functions = None
self.stability_and_control.number_of_control_surfaces = 0
self.conditions.freestream = Data()
self.conditions.freestream.mach = 0.0
self.conditions.freestream.velocity = 0.0
self.conditions.freestream.density = 1.225
self.conditions.freestream.gravitational_acceleration = 9.81
self.conditions.aerodynamics = Data()
self.conditions.aerodynamics.parasite_drag = 0.0
self.conditions.aerodynamics.angles = Data()
self.conditions.aerodynamics.angles.alpha = None
self.conditions.aerodynamics.angles.beta = 0.0
self.conditions.aerodynamics.coefficients = Data()
self.conditions.aerodynamics.coefficients.lift = Data()
self.conditions.aerodynamics.coefficients.lift.total = Data()
self.conditions.static_stability = Data()
self.conditions.static_stability.coefficients = Data()
self.conditions.static_stability.coefficients.roll = 0
self.conditions.static_stability.coefficients.pitch = 0
self.aero_result_filename_1 = None
self.aero_result_filename_2 = None
self.aero_result_filename_3 = None
self.aero_result_filename_4 = None
self.eigen_result_filename_1 = None
self.eigen_result_filename_2 = None
return
[docs]
class Container(DataOrdered):
""" This is a data class for the addition of a cases to the set of run cases
Assumptions:
None
Source:
None
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
[docs]
def append_case(self,case):
""" Adds a case to the set of run cases "
Assumptions:
None
Source:
None
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
case.index = len(self)+1
self.append(case)
return
# ------------------------------------------------------------
# Handle Linking
# ------------------------------------------------------------
Run_Case.Container = Container
