Source code for RCAIDE.Framework.Analyses.Stability.Vortex_Lattice_Method
# RCAIDE/Framework/Analyses/Stability/Vortex_Lattice_Method.py
#
#
# Created: Jul 2023, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
from RCAIDE.Framework.Core import Data, Units
from RCAIDE.Framework.Analyses import Process
from RCAIDE.Library.Methods.Stability import Common
from .Stability import Stability
from RCAIDE.Library.Methods.Stability.Vortex_Lattice_Method import *
import numpy as np
# ----------------------------------------------------------------------------------------------------------------------
# Vortex_Lattice_Method
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Vortex_Lattice_Method(Stability):
"""This is a subsonic aerodynamic buildup analysis based on the vortex lattice method
Assumptions:
Stall effects are negligible
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
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 = 'Vortex_Lattice_Method'
self.vehicle = Data()
self.process = Process()
self.process.initialize = Process()
# correction factors
self.settings.use_surrogate = True
self.settings.propeller_wake_model = False
self.settings.number_of_spanwise_vortices = 30
self.settings.number_of_chordwise_vortices = 15
self.settings.number_of_fuselage_spanwise_vortices = 4
self.settings.number_of_fuselage_chordwise_vortices = 10
self.settings.model_fuselage = True
self.settings.spanwise_cosine_spacing = True
self.settings.vortex_distribution = Data()
self.settings.leading_edge_suction_multiplier = 1.0
self.settings.use_VORLAX_matrix_calculation = False
self.settings.floating_point_precision = np.float32
# conditions table, used for surrogate model training
self.training = Data()
self.training.angle_of_attack = np.array([-5., -2. , 1E-20 , 2.0, 5.0, 8.0, 12., 45., 75.]) * Units.deg
self.training.Mach = np.array([0.1 ,0.3, 0.5, 0.65 , 0.85 , 0.9, 1.3, 1.35 , 1.5 , 2.0, 2.25 , 2.5 , 3.5])
self.training.subsonic = None
self.training.supersonic = None
self.training.transonic = None
# blending function
self.hsub_min = 0.85
self.hsub_max = 0.95
self.hsup_min = 1.05
self.hsup_max = 1.15
# surrogoate models
self.surrogates = Data()
# build the evaluation process
compute = Process()
compute.static_stability = evaluate
compute.dynamic_stability = Common.compute_dynamic_flight_modes
self.process.compute = compute
[docs]
def initialize(self, vehicle):
# compute neutral point
if self.settings.compute_neutral_point:
print("\n Computing neutral point ...")
compute_neutral_point(self, vehicle)
elif vehicle.neutral_point == None:
raise AttributeError('Neutral point not defined.')
return
[docs]
def evaluate(self,state, vehicle):
"""The default evaluate function.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
results <RCAIDE data class>
Properties Used:
self.settings
self.vehicle
"""
settings = self.settings
results = self.process.compute(state,settings,vehicle)
return results
