# RCAIDE/Library/Methods/Aerodynamics/Vortex_Lattice_Method/generate_vortex_distribution.py
#
# Created: May 2018, M. Clarke
# Modified: Apr 2020, M. Clarke
# Jun 2021, A. Blaufox
# ----------------------------------------------------------------------
# Imports
# ----------------------------------------------------------------------
import RCAIDE
from RCAIDE.Framework.Core import Data
from RCAIDE.Library.Methods.Aerodynamics.Vortex_Lattice_Method.postprocess_vortex_distribution import postprocess_vortex_distribution
from RCAIDE.Library.Methods.Aerodynamics.Vortex_Lattice_Method.generate_wing_vortex_distribution import generate_wing_vortex_distribution
from RCAIDE.Library.Methods.Aerodynamics.Vortex_Lattice_Method.generate_fuseform_vortex_distribution import generate_fuseform_vortex_distribution
# package imports
import numpy as np
# ----------------------------------------------------------------------
# Generate Vortex Distribution
# ----------------------------------------------------------------------
[docs]
def generate_vortex_distribution(conditions,settings,geometry):
precision = settings.floating_point_precision
# ---------------------------------------------------------------------------------------
# STEP 1: Define empty vectors for coordinates of panes, control points and bound vortices
# ---------------------------------------------------------------------------------------
VD_seg = Data()
VD_seg.XAH = np.empty(shape=[0,0], dtype=precision)
VD_seg.YAH = np.empty(shape=[0,1], dtype=precision)
VD_seg.ZAH = np.empty(shape=[0,1], dtype=precision)
VD_seg.XBH = np.empty(shape=[0,1], dtype=precision)
VD_seg.YBH = np.empty(shape=[0,1], dtype=precision)
VD_seg.ZBH = np.empty(shape=[0,1], dtype=precision)
VD_seg.XCH = np.empty(shape=[0,1], dtype=precision)
VD_seg.YCH = np.empty(shape=[0,1], dtype=precision)
VD_seg.ZCH = np.empty(shape=[0,1], dtype=precision)
VD_seg.XA1 = np.empty(shape=[0,1], dtype=precision)
VD_seg.YA1 = np.empty(shape=[0,1], dtype=precision)
VD_seg.ZA1 = np.empty(shape=[0,1], dtype=precision)
VD_seg.XA2 = np.empty(shape=[0,1], dtype=precision)
VD_seg.YA2 = np.empty(shape=[0,1], dtype=precision)
VD_seg.ZA2 = np.empty(shape=[0,1], dtype=precision)
VD_seg.XB1 = np.empty(shape=[0,1], dtype=precision)
VD_seg.YB1 = np.empty(shape=[0,1], dtype=precision)
VD_seg.ZB1 = np.empty(shape=[0,1], dtype=precision)
VD_seg.XB2 = np.empty(shape=[0,1], dtype=precision)
VD_seg.YB2 = np.empty(shape=[0,1], dtype=precision)
VD_seg.ZB2 = np.empty(shape=[0,1], dtype=precision)
VD_seg.XAC = np.empty(shape=[0,1], dtype=precision)
VD_seg.YAC = np.empty(shape=[0,1], dtype=precision)
VD_seg.ZAC = np.empty(shape=[0,1], dtype=precision)
VD_seg.XBC = np.empty(shape=[0,1], dtype=precision)
VD_seg.YBC = np.empty(shape=[0,1], dtype=precision)
VD_seg.ZBC = np.empty(shape=[0,1], dtype=precision)
VD_seg.XC_TE = np.empty(shape=[0,1], dtype=precision)
VD_seg.YC_TE = np.empty(shape=[0,1], dtype=precision)
VD_seg.ZC_TE = np.empty(shape=[0,1], dtype=precision)
VD_seg.XA_TE = np.empty(shape=[0,1], dtype=precision)
VD_seg.YA_TE = np.empty(shape=[0,1], dtype=precision)
VD_seg.ZA_TE = np.empty(shape=[0,1], dtype=precision)
VD_seg.XB_TE = np.empty(shape=[0,1], dtype=precision)
VD_seg.YB_TE = np.empty(shape=[0,1], dtype=precision)
VD_seg.ZB_TE = np.empty(shape=[0,1], dtype=precision)
VD_seg.XC = np.empty(shape=[0,1], dtype=precision)
VD_seg.YC = np.empty(shape=[0,1], dtype=precision)
VD_seg.ZC = np.empty(shape=[0,1], dtype=precision)
VD_seg.CS = np.empty(shape=[0,1], dtype=precision)
VD_seg.X = np.empty(shape=[0,1], dtype=precision)
VD_seg.Y = np.empty(shape=[0,1], dtype=precision)
VD_seg.Z = np.empty(shape=[0,1], dtype=precision)
VD_seg.Y_SW = np.empty(shape=[0,1], dtype=precision)
VD_seg.DY = np.empty(shape=[0,1], dtype=precision)
for i in range(len(conditions.aerodynamics.angles.alpha)):
VD_i = generate_aircraft_vortex_distribution(geometry,settings)
if i == 0:
VD_seg.XAH = np.atleast_2d(VD_i.XAH )
VD_seg.YAH = np.atleast_2d(VD_i.YAH )
VD_seg.ZAH = np.atleast_2d(VD_i.ZAH )
VD_seg.XBH = np.atleast_2d(VD_i.XBH )
VD_seg.YBH = np.atleast_2d(VD_i.YBH )
VD_seg.ZBH = np.atleast_2d(VD_i.ZBH )
VD_seg.XCH = np.atleast_2d(VD_i.XCH )
VD_seg.YCH = np.atleast_2d(VD_i.YCH )
VD_seg.ZCH = np.atleast_2d(VD_i.ZCH )
VD_seg.XA1 = np.atleast_2d(VD_i.XA1 )
VD_seg.YA1 = np.atleast_2d(VD_i.YA1 )
VD_seg.ZA1 = np.atleast_2d(VD_i.ZA1 )
VD_seg.XA2 = np.atleast_2d(VD_i.XA2 )
VD_seg.YA2 = np.atleast_2d(VD_i.YA2 )
VD_seg.ZA2 = np.atleast_2d(VD_i.ZA2 )
VD_seg.XB1 = np.atleast_2d(VD_i.XB1 )
VD_seg.YB1 = np.atleast_2d(VD_i.YB1 )
VD_seg.ZB1 = np.atleast_2d(VD_i.ZB1 )
VD_seg.XB2 = np.atleast_2d(VD_i.XB2 )
VD_seg.YB2 = np.atleast_2d(VD_i.YB2 )
VD_seg.ZB2 = np.atleast_2d(VD_i.ZB2 )
VD_seg.XAC = np.atleast_2d(VD_i.XAC )
VD_seg.YAC = np.atleast_2d(VD_i.YAC )
VD_seg.ZAC = np.atleast_2d(VD_i.ZAC )
VD_seg.XBC = np.atleast_2d(VD_i.XBC )
VD_seg.YBC = np.atleast_2d(VD_i.YBC )
VD_seg.ZBC = np.atleast_2d(VD_i.ZBC )
VD_seg.XC_TE = np.atleast_2d(VD_i.XC_TE )
VD_seg.YC_TE = np.atleast_2d(VD_i.YC_TE )
VD_seg.ZC_TE = np.atleast_2d(VD_i.ZC_TE )
VD_seg.XA_TE = np.atleast_2d(VD_i.XA_TE )
VD_seg.YA_TE = np.atleast_2d(VD_i.YA_TE )
VD_seg.ZA_TE = np.atleast_2d(VD_i.ZA_TE )
VD_seg.XB_TE = np.atleast_2d(VD_i.XB_TE )
VD_seg.YB_TE = np.atleast_2d(VD_i.YB_TE )
VD_seg.ZB_TE = np.atleast_2d(VD_i.ZB_TE )
VD_seg.XC = np.atleast_2d(VD_i.XC )
VD_seg.YC = np.atleast_2d(VD_i.YC )
VD_seg.ZC = np.atleast_2d(VD_i.ZC )
VD_seg.CS = np.atleast_2d(VD_i.CS )
VD_seg.X = np.atleast_2d(VD_i.X )
VD_seg.Y = np.atleast_2d(VD_i.Y )
VD_seg.Z = np.atleast_2d(VD_i.Z )
VD_seg.Y_SW = np.atleast_2d(VD_i.Y_SW )
VD_seg.DY = np.atleast_2d(VD_i.DY )
VD_seg.n_w = np.atleast_2d(VD_i.n_w )
VD_seg.n_cp = np.atleast_2d(VD_i.n_cp )
VD_seg.n_sw = np.atleast_2d(VD_i.n_sw )
VD_seg.n_cw = np.atleast_2d(VD_i.n_cw )
VD_seg.chordwise_breaks = np.atleast_2d(VD_i.chordwise_breaks )
VD_seg.spanwise_breaks = np.atleast_2d(VD_i.spanwise_breaks )
VD_seg.symmetric_wings = np.atleast_2d(VD_i.symmetric_wings )
VD_seg.vertical_wing = np.atleast_2d(VD_i.vertical_wing )
VD_seg.surface_ID = np.atleast_2d(VD_i.surface_ID )
VD_seg.surface_ID_full = np.atleast_2d(VD_i.surface_ID_full )
VD_seg.leading_edge_indices = np.atleast_2d(VD_i.leading_edge_indices )
VD_seg.leading_edge_sweeps = np.atleast_2d(VD_i.leading_edge_sweeps )
VD_seg.trailing_edge_indices = np.atleast_2d(VD_i.trailing_edge_indices )
VD_seg.panels_per_strip = np.atleast_2d(VD_i.panels_per_strip )
VD_seg.chordwise_panel_number = np.atleast_2d(VD_i.chordwise_panel_number )
VD_seg.chord_lengths = np.atleast_2d(VD_i.chord_lengths )
VD_seg.chord_widths = np.atleast_2d(VD_i.chord_widths )
VD_seg.tangent_incidence_angle = np.atleast_2d(VD_i.tangent_incidence_angle )
VD_seg.exposed_leading_edge_flag = np.atleast_2d(VD_i.exposed_leading_edge_flag)
VD_seg.wing_areas = np.atleast_2d(VD_i.wing_areas )
VD_seg.vortex_lift = np.atleast_2d(VD_i.vortex_lift )
VD_seg.counter = np.atleast_2d(VD_i.counter )
VD_seg.panel_areas = np.atleast_2d(VD_i.panel_areas )
VD_seg.normals = VD_i.normals[None,:, :]
VD_seg.SLOPE = np.atleast_2d(VD_i.SLOPE )
VD_seg.SLE = np.atleast_2d(VD_i.SLE )
VD_seg.D = np.atleast_2d(VD_i.D )
VD_seg.tangent_incidence_angle = np.atleast_2d(VD_i.tangent_incidence_angle )
else:
VD_seg.XAH = np.vstack(( VD_seg.XAH , np.atleast_2d(VD_i.XAH )))
VD_seg.YAH = np.vstack(( VD_seg.YAH , np.atleast_2d(VD_i.YAH )))
VD_seg.ZAH = np.vstack(( VD_seg.ZAH , np.atleast_2d(VD_i.ZAH )))
VD_seg.XBH = np.vstack(( VD_seg.XBH , np.atleast_2d(VD_i.XBH )))
VD_seg.YBH = np.vstack(( VD_seg.YBH , np.atleast_2d(VD_i.YBH )))
VD_seg.ZBH = np.vstack(( VD_seg.ZBH , np.atleast_2d(VD_i.ZBH )))
VD_seg.XCH = np.vstack(( VD_seg.XCH , np.atleast_2d(VD_i.XCH )))
VD_seg.YCH = np.vstack(( VD_seg.YCH , np.atleast_2d(VD_i.YCH )))
VD_seg.ZCH = np.vstack(( VD_seg.ZCH , np.atleast_2d(VD_i.ZCH )))
VD_seg.XA1 = np.vstack(( VD_seg.XA1 , np.atleast_2d(VD_i.XA1 )))
VD_seg.YA1 = np.vstack(( VD_seg.YA1 , np.atleast_2d(VD_i.YA1 )))
VD_seg.ZA1 = np.vstack(( VD_seg.ZA1 , np.atleast_2d(VD_i.ZA1 )))
VD_seg.XA2 = np.vstack(( VD_seg.XA2 , np.atleast_2d(VD_i.XA2 )))
VD_seg.YA2 = np.vstack(( VD_seg.YA2 , np.atleast_2d(VD_i.YA2 )))
VD_seg.ZA2 = np.vstack(( VD_seg.ZA2 , np.atleast_2d(VD_i.ZA2 )))
VD_seg.XB1 = np.vstack(( VD_seg.XB1 , np.atleast_2d(VD_i.XB1 )))
VD_seg.YB1 = np.vstack(( VD_seg.YB1 , np.atleast_2d(VD_i.YB1 )))
VD_seg.ZB1 = np.vstack(( VD_seg.ZB1 , np.atleast_2d(VD_i.ZB1 )))
VD_seg.XB2 = np.vstack(( VD_seg.XB2 , np.atleast_2d(VD_i.XB2 )))
VD_seg.YB2 = np.vstack(( VD_seg.YB2 , np.atleast_2d(VD_i.YB2 )))
VD_seg.ZB2 = np.vstack(( VD_seg.ZB2 , np.atleast_2d(VD_i.ZB2 )))
VD_seg.XAC = np.vstack(( VD_seg.XAC , np.atleast_2d(VD_i.XAC )))
VD_seg.YAC = np.vstack(( VD_seg.YAC , np.atleast_2d(VD_i.YAC )))
VD_seg.ZAC = np.vstack(( VD_seg.ZAC , np.atleast_2d(VD_i.ZAC )))
VD_seg.XBC = np.vstack(( VD_seg.XBC , np.atleast_2d(VD_i.XBC )))
VD_seg.YBC = np.vstack(( VD_seg.YBC , np.atleast_2d(VD_i.YBC )))
VD_seg.ZBC = np.vstack(( VD_seg.ZBC , np.atleast_2d(VD_i.ZBC )))
VD_seg.XC_TE = np.vstack(( VD_seg.XC_TE, np.atleast_2d(VD_i.XC_TE )))
VD_seg.YC_TE = np.vstack(( VD_seg.YC_TE, np.atleast_2d(VD_i.YC_TE )))
VD_seg.ZC_TE = np.vstack(( VD_seg.ZC_TE, np.atleast_2d(VD_i.ZC_TE )))
VD_seg.XA_TE = np.vstack(( VD_seg.XA_TE, np.atleast_2d(VD_i.XA_TE )))
VD_seg.YA_TE = np.vstack(( VD_seg.YA_TE, np.atleast_2d(VD_i.YA_TE )))
VD_seg.ZA_TE = np.vstack(( VD_seg.ZA_TE, np.atleast_2d(VD_i.ZA_TE )))
VD_seg.XB_TE = np.vstack(( VD_seg.XB_TE, np.atleast_2d(VD_i.XB_TE )))
VD_seg.YB_TE = np.vstack(( VD_seg.YB_TE, np.atleast_2d(VD_i.YB_TE )))
VD_seg.ZB_TE = np.vstack(( VD_seg.ZB_TE, np.atleast_2d(VD_i.ZB_TE )))
VD_seg.XC = np.vstack(( VD_seg.XC , np.atleast_2d(VD_i.XC )))
VD_seg.YC = np.vstack(( VD_seg.YC , np.atleast_2d(VD_i.YC )))
VD_seg.ZC = np.vstack(( VD_seg.ZC , np.atleast_2d(VD_i.ZC )))
VD_seg.CS = np.vstack(( VD_seg.CS , np.atleast_2d(VD_i.CS )))
VD_seg.X = np.vstack(( VD_seg.X , np.atleast_2d(VD_i.X )))
VD_seg.Y = np.vstack(( VD_seg.Y , np.atleast_2d(VD_i.Y )))
VD_seg.Z = np.vstack(( VD_seg.Z , np.atleast_2d(VD_i.Z )))
VD_seg.Y_SW = np.vstack(( VD_seg.Y_SW , np.atleast_2d(VD_i.Y_SW )))
VD_seg.DY = np.vstack(( VD_seg.DY , np.atleast_2d(VD_i.DY )))
VD_seg.n_w = np.vstack((VD_seg.n_w , np.atleast_2d(VD_i.n_w )))
VD_seg.n_cp = np.vstack((VD_seg.n_cp , np.atleast_2d(VD_i.n_cp )))
VD_seg.n_sw = np.vstack((VD_seg.n_sw , np.atleast_2d(VD_i.n_sw )))
VD_seg.n_cw = np.vstack((VD_seg.n_cw , np.atleast_2d(VD_i.n_cw )))
VD_seg.chordwise_breaks = np.vstack((VD_seg.chordwise_breaks , np.atleast_2d(VD_i.chordwise_breaks )))
VD_seg.spanwise_breaks = np.vstack((VD_seg.spanwise_breaks , np.atleast_2d(VD_i.spanwise_breaks )))
VD_seg.symmetric_wings = np.vstack((VD_seg.symmetric_wings , np.atleast_2d(VD_i.symmetric_wings )))
VD_seg.vertical_wing = np.vstack((VD_seg.vertical_wing , np.atleast_2d(VD_i.vertical_wing )))
VD_seg.surface_ID = np.vstack((VD_seg.surface_ID , np.atleast_2d(VD_i.surface_ID )))
VD_seg.surface_ID_full = np.vstack((VD_seg.surface_ID_full , np.atleast_2d(VD_i.surface_ID_full )))
VD_seg.leading_edge_indices = np.vstack((VD_seg.leading_edge_indices , np.atleast_2d(VD_i.leading_edge_indices )))
VD_seg.leading_edge_sweeps = np.vstack((VD_seg.leading_edge_sweeps , np.atleast_2d(VD_i.leading_edge_sweeps )))
VD_seg.trailing_edge_indices = np.vstack((VD_seg.trailing_edge_indices , np.atleast_2d(VD_i.trailing_edge_indices )))
VD_seg.panels_per_strip = np.vstack((VD_seg.panels_per_strip , np.atleast_2d(VD_i.panels_per_strip )))
VD_seg.chordwise_panel_number = np.vstack((VD_seg.chordwise_panel_number , np.atleast_2d(VD_i.chordwise_panel_number )))
VD_seg.chord_lengths = np.vstack((VD_seg.chord_lengths , np.atleast_2d(VD_i.chord_lengths )))
VD_seg.chord_widths = np.vstack((VD_seg.chord_widths , np.atleast_2d(VD_i.chord_widths )))
VD_seg.tangent_incidence_angle = np.vstack((VD_seg.tangent_incidence_angle , np.atleast_2d(VD_i.tangent_incidence_angle )))
VD_seg.exposed_leading_edge_flag = np.vstack((VD_seg.exposed_leading_edge_flag , np.atleast_2d(VD_i.exposed_leading_edge_flag)))
VD_seg.wing_areas = np.vstack((VD_seg.wing_areas , np.atleast_2d(VD_i.wing_areas )))
VD_seg.vortex_lift = np.vstack((VD_seg.vortex_lift , np.atleast_2d(VD_i.vortex_lift )))
VD_seg.counter = np.vstack((VD_seg.counter , np.atleast_2d(VD_i.counter )))
VD_seg.panel_areas = np.vstack((VD_seg.panel_areas , np.atleast_2d(VD_i.panel_areas )))
VD_seg.normals = np.vstack((VD_seg.normals , VD_i.normals[None, :, :] ))
VD_seg.SLOPE = np.vstack((VD_seg.SLOPE , np.atleast_2d(VD_i.SLOPE )))
VD_seg.SLE = np.vstack((VD_seg.SLE , np.atleast_2d(VD_i.SLE )))
VD_seg.D = np.vstack((VD_seg.D , np.atleast_2d(VD_i.D )))
return VD_seg
[docs]
def generate_aircraft_vortex_distribution(geometry,settings):
''' Compute the coordinates of panels, vortices , control points
and geometry used to build the influence coefficient matrix. A
different discretization (n_sw and n_cw) may be defined for each type
of major section (wings and fuselages).
Control surfaces are modelled as wings, but adapt their panel density
to that of the area in which they reside on their own wing.
Assumptions:
Below is a schematic of the coordinates of an arbitrary panel
XA1 ____________________________ XB1
| |
| bound vortex |
XAH| ________________________ |XBH
| | XCH | |
| | | |
| | | |
| | | |
| | | |
| | 0 <--control | |
| | XC point | |
| | | |
XA2 |_|________________________|_|XB2
| |
| trailing |
| <-- vortex --> |
| legs |
In addition, all control surfaces should be appended directly
to the wing, not the wing segments
For control surfaces, "positve" deflection corresponds to the RH rule where the axis of rotation is the OUTBOARD-pointing hinge vector
symmetry: the LH rule is applied to the reflected surface for non-ailerons. Ailerons follow a RH rule for both sides
Source:
None
Inputs:
geometry.wings [Unitless]
settings.floating_point_precision [np.dtype]
Of the following settings, the user should define either the number_ atrributes or the wing_ and fuse_ attributes.
settings.number_of_spanwise_vortices - a base number of vortices to be applied to both wings and fuselages
settings.number_of_chordwise_vortices - a base number of vortices to be applied to both wings and fuselages
Outputs:
VD - vehicle vortex distribution [Unitless]
Properties Used:
N/A
'''
# ---------------------------------------------------------------------------------------
# STEP 0: Unpack settings
# ---------------------------------------------------------------------------------------
#unpack other settings----------------------------------------------------
spc = settings.spanwise_cosine_spacing
precision = settings.floating_point_precision
# unpack discretization settings------------------------------------------
n_sw = settings.number_of_spanwise_vortices
n_cw = settings.number_of_chordwise_vortices
n_sw_f = settings.number_of_fuselage_spanwise_vortices
n_cw_f = settings.number_of_fuselage_chordwise_vortices
# ---------------------------------------------------------------------------------------
# STEP 1: Define empty vectors for coordinates of panes, control points and bound vortices
# ---------------------------------------------------------------------------------------
VD = Data()
VD.XAH = np.empty(shape=[0,1], dtype=precision)
VD.YAH = np.empty(shape=[0,1], dtype=precision)
VD.ZAH = np.empty(shape=[0,1], dtype=precision)
VD.XBH = np.empty(shape=[0,1], dtype=precision)
VD.YBH = np.empty(shape=[0,1], dtype=precision)
VD.ZBH = np.empty(shape=[0,1], dtype=precision)
VD.XCH = np.empty(shape=[0,1], dtype=precision)
VD.YCH = np.empty(shape=[0,1], dtype=precision)
VD.ZCH = np.empty(shape=[0,1], dtype=precision)
VD.XA1 = np.empty(shape=[0,1], dtype=precision)
VD.YA1 = np.empty(shape=[0,1], dtype=precision)
VD.ZA1 = np.empty(shape=[0,1], dtype=precision)
VD.XA2 = np.empty(shape=[0,1], dtype=precision)
VD.YA2 = np.empty(shape=[0,1], dtype=precision)
VD.ZA2 = np.empty(shape=[0,1], dtype=precision)
VD.XB1 = np.empty(shape=[0,1], dtype=precision)
VD.YB1 = np.empty(shape=[0,1], dtype=precision)
VD.ZB1 = np.empty(shape=[0,1], dtype=precision)
VD.XB2 = np.empty(shape=[0,1], dtype=precision)
VD.YB2 = np.empty(shape=[0,1], dtype=precision)
VD.ZB2 = np.empty(shape=[0,1], dtype=precision)
VD.XAC = np.empty(shape=[0,1], dtype=precision)
VD.YAC = np.empty(shape=[0,1], dtype=precision)
VD.ZAC = np.empty(shape=[0,1], dtype=precision)
VD.XBC = np.empty(shape=[0,1], dtype=precision)
VD.YBC = np.empty(shape=[0,1], dtype=precision)
VD.ZBC = np.empty(shape=[0,1], dtype=precision)
VD.XC_TE = np.empty(shape=[0,1], dtype=precision)
VD.YC_TE = np.empty(shape=[0,1], dtype=precision)
VD.ZC_TE = np.empty(shape=[0,1], dtype=precision)
VD.XA_TE = np.empty(shape=[0,1], dtype=precision)
VD.YA_TE = np.empty(shape=[0,1], dtype=precision)
VD.ZA_TE = np.empty(shape=[0,1], dtype=precision)
VD.XB_TE = np.empty(shape=[0,1], dtype=precision)
VD.YB_TE = np.empty(shape=[0,1], dtype=precision)
VD.ZB_TE = np.empty(shape=[0,1], dtype=precision)
VD.XC = np.empty(shape=[0,1], dtype=precision)
VD.YC = np.empty(shape=[0,1], dtype=precision)
VD.ZC = np.empty(shape=[0,1], dtype=precision)
VD.CS = np.empty(shape=[0,1], dtype=precision)
VD.X = np.empty(shape=[0,1], dtype=precision)
VD.Y = np.empty(shape=[0,1], dtype=precision)
VD.Z = np.empty(shape=[0,1], dtype=precision)
VD.Y_SW = np.empty(shape=[0,1], dtype=precision)
VD.DY = np.empty(shape=[0,1], dtype=precision)
# empty vectors necessary for arbitrary discretization dimensions
VD.n_w = 0 # number of wings counter (refers to ALL surfaces)
VD.n_f = 0 # number of fuselage counter (refers to ONLY fuselages)
VD.n_cp = 0 # number of bound vortices (panels) counter
VD.n_sw = np.array([], dtype=np.int16) # array of the number of spanwise strips in each wing
VD.n_cw = np.array([], dtype=np.int16) # array of the number of chordwise panels per strip in each wing
VD.chordwise_breaks = np.array([], dtype=np.int32) # indices of the first panel in every strip (given a list of all panels)
VD.spanwise_breaks = np.array([], dtype=np.int32) # indices of the first strip of panels in a wing (given chordwise_breaks)
VD.symmetric_wings = np.array([], dtype=np.int32)
VD.vertical_wing = np.array([], dtype=np.int32)
VD.surface_ID = np.empty(shape=[0,1], dtype=np.int16)
VD.surface_ID_full = np.empty(shape=[0,1], dtype=np.int16)
VD.leading_edge_indices = np.array([], dtype=bool) # bool array of leading edge indices (all false except for panels at leading edge)
VD.leading_edge_sweeps = np.array([], dtype=bool) # bool array of leading edge indices (all false except for panels at leading edge)
VD.trailing_edge_indices = np.array([], dtype=bool) # bool array of trailing edge indices (all false except for panels at trailing edge)
VD.panels_per_strip = np.array([], dtype=np.int16) # array of the number of panels per strip (RNMAX); this is assigned for all panels
VD.chordwise_panel_number = np.array([], dtype=np.int16) # array of panels' numbers in their strips.
VD.chord_lengths = np.array([], dtype=precision) # Chord length, this is assigned for all panels.
VD.tangent_incidence_angle = np.array([], dtype=precision) # Tangent Incidence Angles of the chordwise strip. LE to TE, ZETA
VD.chord_widths = np.array([], dtype=precision) # Chord width, this is assigned for all panels.
VD.exposed_leading_edge_flag = np.array([], dtype=np.int16) # 0 or 1 per strip. 0 turns off leading edge suction for non-slat control surfaces
# ---------------------------------------------------------------------------------------
# Unpack aircraft wing geometry
# ---------------------------------------------------------------------------------------
VD.wing_areas = [] # instantiate wing areas
VD.vortex_lift = []
VD.counter = 0
for wing in geometry.wings:
VD = generate_wing_vortex_distribution(VD,wing,n_cw,n_sw,spc,precision)
if settings.model_fuselage:
for fuselage in geometry.fuselages:
VD = generate_fuseform_vortex_distribution(VD,fuselage,n_cw_f,n_sw_f,spc,precision)
# ---------------------------------------------------------------------------------------
# Postprocess VD information
# ---------------------------------------------------------------------------------------
VD = postprocess_vortex_distribution(VD, settings)
return VD
