# RCAIDE/Library/Methods/Aerodynamics/Vortex_Lattice_Method/evaluate_VLM.py
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
import RCAIDE
from RCAIDE.Framework.Core import Data, orientation_product
from RCAIDE.Library.Methods.Aerodynamics.Vortex_Lattice_Method.VLM import VLM
from RCAIDE.Library.Methods.Utilities import Cubic_Spline_Blender
from RCAIDE.Library.Mission.Common.Update import orientations
from RCAIDE.Library.Mission.Common.Unpack_Unknowns import orientation
# package imports
import numpy as np
from copy import deepcopy
# ----------------------------------------------------------------------------------------------------------------------
# Vortex_Lattice
# ----------------------------------------------------------------------------------------------------------------------
[docs]
def evaluate_surrogate(state,settings,vehicle):
"""Evaluates surrogates forces and moments using built surrogates
Assumptions:
Source:
None
Args:
aerodynamics : VLM analysis [unitless]
state : flight conditions [unitless]
settings : VLM analysis settings [unitless]
vehicle : vehicle configuration [unitless]
Returns:
None
"""
conditions = state.conditions
aerodynamics = state.analyses.aerodynamics
trim = aerodynamics.settings.trim_aircraft
sub_sur = aerodynamics.surrogates.subsonic
sup_sur = aerodynamics.surrogates.supersonic
trans_sur = aerodynamics.surrogates.transonic
ref_vals = aerodynamics.reference_values
AoA = np.atleast_2d(conditions.aerodynamics.angles.alpha)
Beta = np.atleast_2d(conditions.aerodynamics.angles.beta)
Mach = np.atleast_2d(conditions.freestream.mach_number)
# loop through wings to determine what control surfaces are present
for wing in vehicle.wings:
for control_surface in wing.control_surfaces:
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Aileron:
if trim != True:
conditions.control_surfaces.aileron.deflection[:, 0] = control_surface.deflection
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Elevator:
if trim != True:
conditions.control_surfaces.elevator.deflection[:, 0] = control_surface.deflection
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Rudder:
if trim != True:
conditions.control_surfaces.rudder.deflection[:, 0] = control_surface.deflection
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Slat:
conditions.control_surfaces.slat.deflection[:, 0] = control_surface.deflection
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Flap:
conditions.control_surfaces.flap.deflection[:, 0] = control_surface.deflection
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Spoiler:
conditions.control_surfaces.spoiler.deflection[:, 0] = control_surface.deflection
hsub_min = aerodynamics.hsub_min
hsub_max = aerodynamics.hsub_max
hsup_min = aerodynamics.hsup_min
hsup_max = aerodynamics.hsup_max
# Spline for Subsonic-to-Transonic-to-Supersonic Regimes
sub_trans_spline = Cubic_Spline_Blender(hsub_min,hsub_max)
h_sub = lambda M:sub_trans_spline.compute(M)
sup_trans_spline = Cubic_Spline_Blender(hsup_max, hsup_min)
h_sup = lambda M:sup_trans_spline.compute(M)
u = np.atleast_2d(conditions.freestream.u)
v = np.atleast_2d(conditions.freestream.v)
w = np.atleast_2d(conditions.freestream.w)
p = np.atleast_2d(conditions.static_stability.roll_rate)
q = np.atleast_2d(conditions.static_stability.pitch_rate)
r = np.atleast_2d(conditions.static_stability.yaw_rate)
# -----------------------------------------------------------------------------------------------------------------------
# Query surrogates
# -----------------------------------------------------------------------------------------------------------------------
pts_alpha = np.hstack((AoA,Mach))
pts_beta = np.hstack((Beta,Mach))
pts_u = np.hstack((u,Mach))
pts_v = np.hstack((v,Mach))
pts_w = np.hstack((w,Mach))
pts_p = np.hstack((p,Mach))
pts_q = np.hstack((q,Mach))
pts_r = np.hstack((r,Mach))
# Alpha
results_alpha = compute_coefficients(sub_sur.Clift_alpha, sub_sur.Cdrag_alpha, sub_sur.CX_alpha, sub_sur.CY_alpha, sub_sur.CZ_alpha, sub_sur.CL_alpha, sub_sur.CM_alpha, sub_sur.CN_alpha,
trans_sur.Clift_alpha,trans_sur.Cdrag_alpha,trans_sur.CX_alpha,trans_sur.CY_alpha,trans_sur.CZ_alpha,trans_sur.CL_alpha,trans_sur.CM_alpha, trans_sur.CN_alpha,
sup_sur.Clift_alpha, sup_sur.Cdrag_alpha, sup_sur.CX_alpha, sup_sur.CY_alpha, sup_sur.CZ_alpha, sup_sur.CL_alpha, sup_sur.CM_alpha, sup_sur.CN_alpha,
h_sub,h_sup,Mach, pts_alpha)
Clift_alpha = results_alpha.Clift
Cdrag_alpha = results_alpha.Cdrag
CX_alpha = results_alpha.CX
CY_alpha = results_alpha.CY
CZ_alpha = results_alpha.CZ
CL_alpha = results_alpha.CL
CM_alpha = results_alpha.CM
CN_alpha = results_alpha.CN
Clift_alpha[AoA==0.0] = 0
Cdrag_alpha[AoA==0.0] = 0
CX_alpha[AoA==0.0] = 0
CY_alpha[AoA==0.0] = 0
CZ_alpha[AoA==0.0] = 0
CL_alpha[AoA==0.0] = 0
CM_alpha[AoA==0.0] = 0
CN_alpha[AoA==0.0] = 0
# Beta
results_beta = compute_coefficients(sub_sur.Clift_beta, sub_sur.Cdrag_beta, sub_sur.CX_beta, sub_sur.CY_beta, sub_sur.CZ_beta, sub_sur.CL_beta, sub_sur.CM_beta, sub_sur.CN_beta,
trans_sur.Clift_beta,trans_sur.Cdrag_beta,trans_sur.CX_beta,trans_sur.CY_beta,trans_sur.CZ_beta,trans_sur.CL_beta,trans_sur.CM_beta, trans_sur.CN_beta,
sup_sur.Clift_beta, sup_sur.Cdrag_beta, sup_sur.CX_beta, sup_sur.CY_beta, sup_sur.CZ_beta, sup_sur.CL_beta, sup_sur.CM_beta, sup_sur.CN_beta,
h_sub,h_sup,Mach, pts_beta)
Clift_beta = results_beta.Clift
Cdrag_beta = results_beta.Cdrag
CX_beta = results_beta.CX
CY_beta = results_beta.CY
CZ_beta = results_beta.CZ
CL_beta = results_beta.CL
CM_beta = results_beta.CM
CN_beta = results_beta.CN
Clift_beta[Beta==0.0] = 0
Cdrag_beta[Beta==0.0] = 0
CX_beta[Beta==0.0] = 0
CY_beta[Beta==0.0] = 0
CZ_beta[Beta==0.0] = 0
CL_beta[Beta==0.0] = 0
CM_beta[Beta==0.0] = 0
CN_beta[Beta==0.0] = 0
# u
results_u = compute_coefficients(sub_sur.Clift_u, sub_sur.Cdrag_u, sub_sur.CX_u, sub_sur.CY_u, sub_sur.CZ_u, sub_sur.CL_u, sub_sur.CM_u, sub_sur.CN_u,
trans_sur.Clift_u,trans_sur.Cdrag_u,trans_sur.CX_u,trans_sur.CY_u,trans_sur.CZ_u,trans_sur.CL_u,trans_sur.CM_u, trans_sur.CN_u,
sup_sur.Clift_u, sup_sur.Cdrag_u, sup_sur.CX_u, sup_sur.CY_u, sup_sur.CZ_u, sup_sur.CL_u, sup_sur.CM_u, sup_sur.CN_u,
h_sub,h_sup,Mach, pts_u)
Clift_u = results_u.Clift
Cdrag_u = results_u.Cdrag
CX_u = results_u.CX
CY_u = results_u.CY
CZ_u = results_u.CZ
CL_u = results_u.CL
CM_u = results_u.CM
CN_u = results_u.CN
Clift_u[u==0.0] = 0
Cdrag_u[u==0.0] = 0
CX_u[u==0.0] = 0
CY_u[u==0.0] = 0
CZ_u[u==0.0] = 0
CL_u[u==0.0] = 0
CM_u[u==0.0] = 0
CN_u[u==0.0] = 0
# v
results_v = compute_coefficients(sub_sur.Clift_v, sub_sur.Cdrag_v, sub_sur.CX_v, sub_sur.CY_v, sub_sur.CZ_v, sub_sur.CL_v, sub_sur.CM_v, sub_sur.CN_v,
trans_sur.Clift_v,trans_sur.Cdrag_v,trans_sur.CX_v,trans_sur.CY_v,trans_sur.CZ_v,trans_sur.CL_v,trans_sur.CM_v, trans_sur.CN_v,
sup_sur.Clift_v, sup_sur.Cdrag_v, sup_sur.CX_v, sup_sur.CY_v, sup_sur.CZ_v, sup_sur.CL_v, sup_sur.CM_v, sup_sur.CN_v,
h_sub,h_sup,Mach, pts_v)
Clift_v = results_v.Clift
Cdrag_v = results_v.Cdrag
CX_v = results_v.CX
CY_v = results_v.CY
CZ_v = results_v.CZ
CL_v = results_v.CL
CM_v = results_v.CM
CN_v = results_v.CN
Clift_v[v==0.0] = 0
Cdrag_v[v==0.0] = 0
CX_v[v==0.0] = 0
CY_v[v==0.0] = 0
CZ_v[v==0.0] = 0
CL_v[v==0.0] = 0
CM_v[v==0.0] = 0
CN_v[v==0.0] = 0
# w
results_w = compute_coefficients(sub_sur.Clift_w, sub_sur.Cdrag_w, sub_sur.CX_w, sub_sur.CY_w, sub_sur.CZ_w, sub_sur.CL_w, sub_sur.CM_w, sub_sur.CN_w,
trans_sur.Clift_w,trans_sur.Cdrag_w,trans_sur.CX_w,trans_sur.CY_w,trans_sur.CZ_w,trans_sur.CL_w,trans_sur.CM_w, trans_sur.CN_w,
sup_sur.Clift_w, sup_sur.Cdrag_w, sup_sur.CX_w, sup_sur.CY_w, sup_sur.CZ_w, sup_sur.CL_w, sup_sur.CM_w, sup_sur.CN_w,
h_sub,h_sup,Mach, pts_w)
Clift_w = results_w.Clift
Cdrag_w = results_w.Cdrag
CX_w = results_w.CX
CY_w = results_w.CY
CZ_w = results_w.CZ
CL_w = results_w.CL
CM_w = results_w.CM
CN_w = results_w.CN
Clift_w[w==0.0] = 0
Cdrag_w[w==0.0] = 0
CX_w[w==0.0] = 0
CY_w[w==0.0] = 0
CZ_w[w==0.0] = 0
CL_w[w==0.0] = 0
CM_w[w==0.0] = 0
CN_w[w==0.0] = 0
# p
results_p = compute_coefficients(sub_sur.Clift_p, sub_sur.Cdrag_p, sub_sur.CX_p, sub_sur.CY_p, sub_sur.CZ_p, sub_sur.CL_p, sub_sur.CM_p, sub_sur.CN_p,
trans_sur.Clift_p,trans_sur.Cdrag_p,trans_sur.CX_p,trans_sur.CY_p,trans_sur.CZ_p,trans_sur.CL_p,trans_sur.CM_p, trans_sur.CN_p,
sup_sur.Clift_p, sup_sur.Cdrag_p, sup_sur.CX_p, sup_sur.CY_p, sup_sur.CZ_p, sup_sur.CL_p, sup_sur.CM_p, sup_sur.CN_p,
h_sub,h_sup,Mach, pts_p)
Clift_p = results_p.Clift
Cdrag_p = results_p.Cdrag
CX_p = results_p.CX
CY_p = results_p.CY
CZ_p = results_p.CZ
CL_p = results_p.CL
CM_p = results_p.CM
CN_p = results_p.CN
Clift_p[p==0.0] = 0
Cdrag_p[p==0.0] = 0
CX_p[p==0.0] = 0
CY_p[p==0.0] = 0
CZ_p[p==0.0] = 0
CL_p[p==0.0] = 0
CM_p[p==0.0] = 0
CN_p[p==0.0] = 0
# q
results_q = compute_coefficients(sub_sur.Clift_q, sub_sur.Cdrag_q, sub_sur.CX_q, sub_sur.CY_q, sub_sur.CZ_q, sub_sur.CL_q, sub_sur.CM_q, sub_sur.CN_q,
trans_sur.Clift_q,trans_sur.Cdrag_q,trans_sur.CX_q,trans_sur.CY_q,trans_sur.CZ_q,trans_sur.CL_q,trans_sur.CM_q, trans_sur.CN_q,
sup_sur.Clift_q, sup_sur.Cdrag_q, sup_sur.CX_q, sup_sur.CY_q, sup_sur.CZ_q, sup_sur.CL_q, sup_sur.CM_q, sup_sur.CN_q,
h_sub,h_sup,Mach, pts_q)
Clift_q = results_q.Clift
Cdrag_q = results_q.Cdrag
CX_q = results_q.CX
CY_q = results_q.CY
CZ_q = results_q.CZ
CL_q = results_q.CL
CM_q = results_q.CM
CN_q = results_q.CN
Clift_q[q==0.0] = 0
Cdrag_q[q==0.0] = 0
CX_q[q==0.0] = 0
CY_q[q==0.0] = 0
CZ_q[q==0.0] = 0
CL_q[q==0.0] = 0
CM_q[q==0.0] = 0
CN_q[q==0.0] = 0
# r
results_r = compute_coefficients(sub_sur.Clift_r, sub_sur.Cdrag_r, sub_sur.CX_r, sub_sur.CY_r, sub_sur.CZ_r, sub_sur.CL_r, sub_sur.CM_r, sub_sur.CN_r,
trans_sur.Clift_r,trans_sur.Cdrag_r,trans_sur.CX_r,trans_sur.CY_r,trans_sur.CZ_r,trans_sur.CL_r,trans_sur.CM_r, trans_sur.CN_r,
sup_sur.Clift_r, sup_sur.Cdrag_r, sup_sur.CX_r, sup_sur.CY_r, sup_sur.CZ_r, sup_sur.CL_r, sup_sur.CM_r, sup_sur.CN_r,
h_sub,h_sup,Mach, pts_r)
Clift_r = results_r.Clift
Cdrag_r = results_r.Cdrag
CX_r = results_r.CX
CY_r = results_r.CY
CZ_r = results_r.CZ
CL_r = results_r.CL
CM_r = results_r.CM
CN_r = results_r.CN
Clift_r[r==0.0] = 0
Cdrag_r[r==0.0] = 0
CX_r[r==0.0] = 0
CY_r[r==0.0] = 0
CZ_r[r==0.0] = 0
CL_r[r==0.0] = 0
CM_r[r==0.0] = 0
CN_r[r==0.0] = 0
# -----------------------------------------------------------------------------------------------------------------------
# Stability Results Without Control Surfaces
# -----------------------------------------------------------------------------------------------------------------------
conditions.S_ref = ref_vals.S_ref
conditions.c_ref = ref_vals.c_ref
conditions.b_ref = ref_vals.b_ref
conditions.X_ref = ref_vals.X_ref
conditions.Y_ref = ref_vals.Y_ref
conditions.Z_ref = ref_vals.Z_ref
conditions.static_stability.coefficients.lift = Clift_alpha + Clift_u + Clift_w + Clift_q
conditions.static_stability.coefficients.drag = Cdrag_alpha + Cdrag_u + Cdrag_w + Cdrag_q
conditions.static_stability.coefficients.X = CX_alpha + CX_u + CX_w + CX_q
conditions.static_stability.coefficients.Y = CY_beta + CY_v + CY_p + CY_r
conditions.static_stability.coefficients.Z = CZ_alpha + CZ_u + CZ_w + CZ_q
conditions.static_stability.coefficients.L = CL_beta + CL_v + CL_p +CL_r
conditions.static_stability.coefficients.M = CM_alpha + CM_u + CM_w + CM_q
conditions.static_stability.coefficients.N = CN_beta + CN_v + CN_p + CN_r
# -----------------------------------------------------------------------------------------------------------------------
# Addition of Control Surface Effect
# -----------------------------------------------------------------------------------------------------------------------
if aerodynamics.aileron_flag:
pts_delta_a = np.hstack((conditions.control_surfaces.aileron.deflection,Mach))
results_delta_a = compute_coefficients(sub_sur.Clift_delta_a,sub_sur.Cdrag_delta_a,sub_sur.CX_delta_a,sub_sur.CY_delta_a,sub_sur.CZ_delta_a,sub_sur.CL_delta_a,sub_sur.CM_delta_a, sub_sur.CN_delta_a,
trans_sur.Clift_delta_a,trans_sur.Cdrag_delta_a,trans_sur.CX_delta_a,trans_sur.CY_delta_a,trans_sur.CZ_delta_a,trans_sur.CL_delta_a,trans_sur.CM_delta_a, trans_sur.CN_delta_a,
sup_sur.Clift_delta_a,sup_sur.Cdrag_delta_a,sup_sur.CX_delta_a,sup_sur.CY_delta_a,sup_sur.CZ_delta_a,sup_sur.CL_delta_a,sup_sur.CM_delta_a, sup_sur.CN_delta_a,
h_sub,h_sup,Mach, pts_delta_a)
Clift_delta_a = results_delta_a.Clift
Cdrag_delta_a = results_delta_a.Cdrag
CX_delta_a = results_delta_a.CX
CY_delta_a = results_delta_a.CY
CZ_delta_a = results_delta_a.CZ
CL_delta_a = results_delta_a.CL
CM_delta_a = results_delta_a.CM
CN_delta_a = results_delta_a.CN
Clift_delta_a[conditions.control_surfaces.aileron.deflection==0.0] = 0
Cdrag_delta_a[conditions.control_surfaces.aileron.deflection==0.0] = 0
CX_delta_a[conditions.control_surfaces.aileron.deflection==0.0] = 0
CY_delta_a[conditions.control_surfaces.aileron.deflection==0.0] = 0
CZ_delta_a[conditions.control_surfaces.aileron.deflection==0.0] = 0
CL_delta_a[conditions.control_surfaces.aileron.deflection==0.0] = 0
CM_delta_a[conditions.control_surfaces.aileron.deflection==0.0] = 0
CN_delta_a[conditions.control_surfaces.aileron.deflection==0.0] = 0
conditions.static_stability.coefficients.lift += Clift_delta_a
conditions.static_stability.coefficients.drag += Cdrag_delta_a
conditions.static_stability.coefficients.X += CX_delta_a
conditions.static_stability.coefficients.Y += CY_delta_a
conditions.static_stability.coefficients.Z += CZ_delta_a
conditions.static_stability.coefficients.L += CL_delta_a
conditions.static_stability.coefficients.M += CM_delta_a
conditions.static_stability.coefficients.N += CN_delta_a
conditions.control_surfaces.aileron.static_stability.coefficients.lift = Clift_delta_a
conditions.control_surfaces.aileron.static_stability.coefficients.drag = Cdrag_delta_a
conditions.control_surfaces.aileron.static_stability.coefficients.X = CX_delta_a
conditions.control_surfaces.aileron.static_stability.coefficients.Y = CY_delta_a
conditions.control_surfaces.aileron.static_stability.coefficients.Z = CZ_delta_a
conditions.control_surfaces.aileron.static_stability.coefficients.L = CL_delta_a
conditions.control_surfaces.aileron.static_stability.coefficients.M = CM_delta_a
conditions.control_surfaces.aileron.static_stability.coefficients.N = CN_delta_a
if aerodynamics.elevator_flag:
pts_delta_e = np.hstack((conditions.control_surfaces.elevator.deflection,Mach))
results_delta_e = compute_coefficients(sub_sur.Clift_delta_e,sub_sur.Cdrag_delta_e,sub_sur.CX_delta_e,sub_sur.CY_delta_e,sub_sur.CZ_delta_e,sub_sur.CL_delta_e,sub_sur.CM_delta_e, sub_sur.CN_delta_e,
trans_sur.Clift_delta_e,trans_sur.Cdrag_delta_e,trans_sur.CX_delta_e,trans_sur.CY_delta_e,trans_sur.CZ_delta_e,trans_sur.CL_delta_e,trans_sur.CM_delta_e, trans_sur.CN_delta_e,
sup_sur.Clift_delta_e,sup_sur.Cdrag_delta_e,sup_sur.CX_delta_e,sup_sur.CY_delta_e,sup_sur.CZ_delta_e,sup_sur.CL_delta_e,sup_sur.CM_delta_e, sup_sur.CN_delta_e,
h_sub,h_sup,Mach, pts_delta_e)
Clift_delta_e = results_delta_e.Clift
Cdrag_delta_e = results_delta_e.Cdrag
CX_delta_e = results_delta_e.CX
CY_delta_e = results_delta_e.CY
CZ_delta_e = results_delta_e.CZ
CL_delta_e = results_delta_e.CL
CM_delta_e = results_delta_e.CM
CN_delta_e = results_delta_e.CN
Clift_delta_e[conditions.control_surfaces.elevator.deflection==0.0] = 0
Cdrag_delta_e[conditions.control_surfaces.elevator.deflection==0.0] = 0
CX_delta_e[conditions.control_surfaces.elevator.deflection==0.0] = 0
CY_delta_e[conditions.control_surfaces.elevator.deflection==0.0] = 0
CZ_delta_e[conditions.control_surfaces.elevator.deflection==0.0] = 0
CL_delta_e[conditions.control_surfaces.elevator.deflection==0.0] = 0
CM_delta_e[conditions.control_surfaces.elevator.deflection==0.0] = 0
CN_delta_e[conditions.control_surfaces.elevator.deflection==0.0] = 0
conditions.static_stability.coefficients.lift += Clift_delta_e
conditions.static_stability.coefficients.drag += Cdrag_delta_e
conditions.static_stability.coefficients.X += CX_delta_e
conditions.static_stability.coefficients.Y += CY_delta_e
conditions.static_stability.coefficients.Z += CZ_delta_e
conditions.static_stability.coefficients.L += CL_delta_e
conditions.static_stability.coefficients.M += CM_delta_e
conditions.static_stability.coefficients.N += CN_delta_e
conditions.control_surfaces.elevator.static_stability.coefficients.lift = Clift_delta_e
conditions.control_surfaces.elevator.static_stability.coefficients.drag = Cdrag_delta_e
conditions.control_surfaces.elevator.static_stability.coefficients.X = CX_delta_e
conditions.control_surfaces.elevator.static_stability.coefficients.Y = CY_delta_e
conditions.control_surfaces.elevator.static_stability.coefficients.Z = CZ_delta_e
conditions.control_surfaces.elevator.static_stability.coefficients.L = CL_delta_e
conditions.control_surfaces.elevator.static_stability.coefficients.M = CM_delta_e
conditions.control_surfaces.elevator.static_stability.coefficients.N = CN_delta_e
if aerodynamics.rudder_flag:
pts_delta_r = np.hstack((conditions.control_surfaces.rudder.deflection,Mach))
results_delta_r = compute_coefficients(sub_sur.Clift_delta_r,sub_sur.Cdrag_delta_r,sub_sur.CX_delta_r,sub_sur.CY_delta_r,sub_sur.CZ_delta_r,sub_sur.CL_delta_r,sub_sur.CM_delta_r, sub_sur.CN_delta_r,
trans_sur.Clift_delta_r,trans_sur.Cdrag_delta_r,trans_sur.CX_delta_r,trans_sur.CY_delta_r,trans_sur.CZ_delta_r,trans_sur.CL_delta_r,trans_sur.CM_delta_r, trans_sur.CN_delta_r,
sup_sur.Clift_delta_r,sup_sur.Cdrag_delta_r,sup_sur.CX_delta_r,sup_sur.CY_delta_r,sup_sur.CZ_delta_r,sup_sur.CL_delta_r,sup_sur.CM_delta_r, sup_sur.CN_delta_r,
h_sub,h_sup,Mach, pts_delta_r)
Clift_delta_r = results_delta_r.Clift
Cdrag_delta_r = results_delta_r.Cdrag
CX_delta_r = results_delta_r.CX
CY_delta_r = results_delta_r.CY
CZ_delta_r = results_delta_r.CZ
CL_delta_r = results_delta_r.CL
CM_delta_r = results_delta_r.CM
CN_delta_r = results_delta_r.CN
Clift_delta_r[conditions.control_surfaces.rudder.deflection==0.0] = 0
Cdrag_delta_r[conditions.control_surfaces.rudder.deflection==0.0] = 0
CX_delta_r[conditions.control_surfaces.rudder.deflection==0.0] = 0
CY_delta_r[conditions.control_surfaces.rudder.deflection==0.0] = 0
CZ_delta_r[conditions.control_surfaces.rudder.deflection==0.0] = 0
CL_delta_r[conditions.control_surfaces.rudder.deflection==0.0] = 0
CM_delta_r[conditions.control_surfaces.rudder.deflection==0.0] = 0
CN_delta_r[conditions.control_surfaces.rudder.deflection==0.0] = 0
conditions.static_stability.coefficients.lift += Clift_delta_r
conditions.static_stability.coefficients.drag += Cdrag_delta_r
conditions.static_stability.coefficients.X += CX_delta_r
conditions.static_stability.coefficients.Y += CY_delta_r
conditions.static_stability.coefficients.Z += CZ_delta_r
conditions.static_stability.coefficients.L += CL_delta_r
conditions.static_stability.coefficients.M += CM_delta_r
conditions.static_stability.coefficients.N += CN_delta_r
conditions.control_surfaces.rudder.static_stability.coefficients.lift = Clift_delta_r
conditions.control_surfaces.rudder.static_stability.coefficients.drag = Cdrag_delta_r
conditions.control_surfaces.rudder.static_stability.coefficients.X = CX_delta_r
conditions.control_surfaces.rudder.static_stability.coefficients.Y = CY_delta_r
conditions.control_surfaces.rudder.static_stability.coefficients.Z = CZ_delta_r
conditions.control_surfaces.rudder.static_stability.coefficients.L = CL_delta_r
conditions.control_surfaces.rudder.static_stability.coefficients.M = CM_delta_r
conditions.control_surfaces.rudder.static_stability.coefficients.N = CN_delta_r
if aerodynamics.flap_flag:
pts_delta_f = np.hstack((conditions.control_surfaces.flap.deflection,Mach))
results_delta_f = compute_coefficients(sub_sur.Clift_delta_f,sub_sur.Cdrag_delta_f,sub_sur.CX_delta_f,sub_sur.CY_delta_f,sub_sur.CZ_delta_f,sub_sur.CL_delta_f,sub_sur.CM_delta_f, sub_sur.CN_delta_f,
trans_sur.Clift_delta_f,trans_sur.Cdrag_delta_f,trans_sur.CX_delta_f,trans_sur.CY_delta_f,trans_sur.CZ_delta_f,trans_sur.CL_delta_f,trans_sur.CM_delta_f, trans_sur.CN_delta_f,
sup_sur.Clift_delta_f,sup_sur.Cdrag_delta_f,sup_sur.CX_delta_f,sup_sur.CY_delta_f,sup_sur.CZ_delta_f,sup_sur.CL_delta_f,sup_sur.CM_delta_f, sup_sur.CN_delta_f,
h_sub,h_sup,Mach, pts_delta_f)
Clift_delta_f = results_delta_f.Clift
Cdrag_delta_f = results_delta_f.Cdrag
CX_delta_f = results_delta_f.CX
CY_delta_f = results_delta_f.CY
CZ_delta_f = results_delta_f.CZ
CL_delta_f = results_delta_f.CL
CM_delta_f = results_delta_f.CM
CN_delta_f = results_delta_f.CN
Clift_delta_f[conditions.control_surfaces.flap.deflection==0.0] = 0
Cdrag_delta_f[conditions.control_surfaces.flap.deflection==0.0] = 0
CX_delta_f[conditions.control_surfaces.flap.deflection==0.0] = 0
CY_delta_f[conditions.control_surfaces.flap.deflection==0.0] = 0
CZ_delta_f[conditions.control_surfaces.flap.deflection==0.0] = 0
CL_delta_f[conditions.control_surfaces.flap.deflection==0.0] = 0
CM_delta_f[conditions.control_surfaces.flap.deflection==0.0] = 0
CN_delta_f[conditions.control_surfaces.flap.deflection==0.0] = 0
conditions.static_stability.coefficients.lift += Clift_delta_f
conditions.static_stability.coefficients.drag += Cdrag_delta_f
conditions.static_stability.coefficients.X += CX_delta_f
conditions.static_stability.coefficients.Y += CY_delta_f
conditions.static_stability.coefficients.Z += CZ_delta_f
conditions.static_stability.coefficients.L += CL_delta_f
conditions.static_stability.coefficients.M += CM_delta_f
conditions.static_stability.coefficients.N += CN_delta_f
conditions.control_surfaces.flap.static_stability.coefficients.lift = Clift_delta_f
conditions.control_surfaces.flap.static_stability.coefficients.drag = Cdrag_delta_f
conditions.control_surfaces.flap.static_stability.coefficients.X = CX_delta_f
conditions.control_surfaces.flap.static_stability.coefficients.Y = CY_delta_f
conditions.control_surfaces.flap.static_stability.coefficients.Z = CZ_delta_f
conditions.control_surfaces.flap.static_stability.coefficients.L = CL_delta_f
conditions.control_surfaces.flap.static_stability.coefficients.M = CM_delta_f
conditions.control_surfaces.flap.static_stability.coefficients.N = CN_delta_f
if aerodynamics.slat_flag:
pts_delta_s = np.hstack((conditions.control_surfaces.slat.deflection,Mach))
results_delta_s = compute_coefficients(sub_sur.Clift_delta_s,sub_sur.Cdrag_delta_s,sub_sur.CX_delta_s,sub_sur.CY_delta_s,sub_sur.CZ_delta_s,sub_sur.CL_delta_s,sub_sur.CM_delta_s, sub_sur.CN_delta_s,
trans_sur.Clift_delta_s,trans_sur.Cdrag_delta_s,trans_sur.CX_delta_s,trans_sur.CY_delta_s,trans_sur.CZ_delta_s,trans_sur.CL_delta_s,trans_sur.CM_delta_s, trans_sur.CN_delta_s,
sup_sur.Clift_delta_s,sup_sur.Cdrag_delta_s,sup_sur.CX_delta_s,sup_sur.CY_delta_s,sup_sur.CZ_delta_s,sup_sur.CL_delta_s,sup_sur.CM_delta_s, sup_sur.CN_delta_s,
h_sub,h_sup,Mach, pts_delta_s)
Clift_delta_s = results_delta_s.Clift
Cdrag_delta_s = results_delta_s.Cdrag
CX_delta_s = results_delta_s.CX
CY_delta_s = results_delta_s.CY
CZ_delta_s = results_delta_s.CZ
CL_delta_s = results_delta_s.CL
CM_delta_s = results_delta_s.CM
CN_delta_s = results_delta_s.CN
Clift_delta_s[conditions.control_surfaces.slat.deflection==0.0] = 0
Cdrag_delta_s[conditions.control_surfaces.slat.deflection==0.0] = 0
CX_delta_s[conditions.control_surfaces.slat.deflection==0.0] = 0
CY_delta_s[conditions.control_surfaces.slat.deflection==0.0] = 0
CZ_delta_s[conditions.control_surfaces.slat.deflection==0.0] = 0
CL_delta_s[conditions.control_surfaces.slat.deflection==0.0] = 0
CM_delta_s[conditions.control_surfaces.slat.deflection==0.0] = 0
CN_delta_s[conditions.control_surfaces.slat.deflection==0.0] = 0
conditions.static_stability.coefficients.lift += Clift_delta_s
conditions.static_stability.coefficients.drag += Cdrag_delta_s
conditions.static_stability.coefficients.X += CX_delta_s
conditions.static_stability.coefficients.Y += CY_delta_s
conditions.static_stability.coefficients.Z += CZ_delta_s
conditions.static_stability.coefficients.L += CL_delta_s
conditions.static_stability.coefficients.M += CM_delta_s
conditions.static_stability.coefficients.N += CN_delta_s
conditions.control_surfaces.slat.static_stability.coefficients.lift = Clift_delta_s
conditions.control_surfaces.slat.static_stability.coefficients.drag = Cdrag_delta_s
conditions.control_surfaces.slat.static_stability.coefficients.X = CX_delta_s
conditions.control_surfaces.slat.static_stability.coefficients.Y = CY_delta_s
conditions.control_surfaces.slat.static_stability.coefficients.Z = CZ_delta_s
conditions.control_surfaces.slat.static_stability.coefficients.L = CL_delta_s
conditions.control_surfaces.slat.static_stability.coefficients.M = CM_delta_s
conditions.control_surfaces.slat.static_stability.coefficients.N = CN_delta_s
conditions.static_stability.derivatives.Clift_alpha = compute_stability_derivative(sub_sur.dClift_dalpha ,trans_sur.dClift_dalpha ,sup_sur.dClift_dalpha ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CX_alpha = compute_stability_derivative(sub_sur.dCX_dalpha ,trans_sur.dCX_dalpha ,sup_sur.dCX_dalpha ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CY_alpha = compute_stability_derivative(sub_sur.dCY_dalpha ,trans_sur.dCY_dalpha ,sup_sur.dCY_dalpha ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CZ_alpha = compute_stability_derivative(sub_sur.dCZ_dalpha ,trans_sur.dCZ_dalpha ,sup_sur.dCZ_dalpha ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CL_alpha = compute_stability_derivative(sub_sur.dCL_dalpha ,trans_sur.dCL_dalpha ,sup_sur.dCL_dalpha ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CM_alpha = compute_stability_derivative(sub_sur.dCM_dalpha ,trans_sur.dCM_dalpha ,sup_sur.dCM_dalpha ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CN_alpha = compute_stability_derivative(sub_sur.dCN_dalpha ,trans_sur.dCN_dalpha ,sup_sur.dCN_dalpha ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.Clift_beta = compute_stability_derivative(sub_sur.dClift_dbeta ,trans_sur.dClift_dbeta ,sup_sur.dClift_dbeta ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CX_beta = compute_stability_derivative(sub_sur.dCX_dbeta ,trans_sur.dCX_dbeta ,sup_sur.dCX_dbeta ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CY_beta = compute_stability_derivative(sub_sur.dCY_dbeta ,trans_sur.dCY_dbeta ,sup_sur.dCY_dbeta ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CZ_beta = compute_stability_derivative(sub_sur.dCZ_dbeta ,trans_sur.dCZ_dbeta ,sup_sur.dCZ_dbeta ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CL_beta = compute_stability_derivative(sub_sur.dCL_dbeta ,trans_sur.dCL_dbeta ,sup_sur.dCL_dbeta ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CM_beta = compute_stability_derivative(sub_sur.dCM_dbeta ,trans_sur.dCM_dbeta ,sup_sur.dCM_dbeta ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CN_beta = compute_stability_derivative(sub_sur.dCN_dbeta ,trans_sur.dCN_dbeta ,sup_sur.dCN_dbeta ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.Clift_p = compute_stability_derivative(sub_sur.dClift_dp ,trans_sur.dClift_dp ,sup_sur.dClift_dp ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.Clift_q = compute_stability_derivative(sub_sur.dClift_dq ,trans_sur.dClift_dq ,sup_sur.dClift_dq ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.Clift_r = compute_stability_derivative(sub_sur.dClift_dr ,trans_sur.dClift_dr ,sup_sur.dClift_dr ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CX_u = compute_stability_derivative(sub_sur.dCX_du ,trans_sur.dCX_du ,sup_sur.dCX_du ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CX_v = compute_stability_derivative(sub_sur.dCX_dv ,trans_sur.dCX_dv ,sup_sur.dCX_dv ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CX_w = compute_stability_derivative(sub_sur.dCX_dw ,trans_sur.dCX_dw ,sup_sur.dCX_dw ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CY_u = compute_stability_derivative(sub_sur.dCY_du ,trans_sur.dCY_du ,sup_sur.dCY_du ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CY_v = compute_stability_derivative(sub_sur.dCY_dv ,trans_sur.dCY_dv ,sup_sur.dCY_dv ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CY_w = compute_stability_derivative(sub_sur.dCY_dw ,trans_sur.dCY_dw ,sup_sur.dCY_dw ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CZ_u = compute_stability_derivative(sub_sur.dCZ_du ,trans_sur.dCZ_du ,sup_sur.dCZ_du ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CZ_v = compute_stability_derivative(sub_sur.dCZ_dv ,trans_sur.dCZ_dv ,sup_sur.dCZ_dv ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CZ_w = compute_stability_derivative(sub_sur.dCZ_dw ,trans_sur.dCZ_dw ,sup_sur.dCZ_dw ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CL_u = compute_stability_derivative(sub_sur.dCL_du ,trans_sur.dCL_du ,sup_sur.dCL_du ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CL_v = compute_stability_derivative(sub_sur.dCL_dv ,trans_sur.dCL_dv ,sup_sur.dCL_dv ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CL_w = compute_stability_derivative(sub_sur.dCL_dw ,trans_sur.dCL_dw ,sup_sur.dCL_dw ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CM_u = compute_stability_derivative(sub_sur.dCM_du ,trans_sur.dCM_du ,sup_sur.dCM_du ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CM_v = compute_stability_derivative(sub_sur.dCM_dv ,trans_sur.dCM_dv ,sup_sur.dCM_dv ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CM_w = compute_stability_derivative(sub_sur.dCM_dw ,trans_sur.dCM_dw ,sup_sur.dCM_dw ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CN_u = compute_stability_derivative(sub_sur.dCN_du ,trans_sur.dCN_du ,sup_sur.dCN_du ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CN_v = compute_stability_derivative(sub_sur.dCN_dv ,trans_sur.dCN_dv ,sup_sur.dCN_dv ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CN_w = compute_stability_derivative(sub_sur.dCN_dw ,trans_sur.dCN_dw ,sup_sur.dCN_dw ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CX_p = compute_stability_derivative(sub_sur.dCX_dp ,trans_sur.dCX_dp ,sup_sur.dCX_dp ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CX_q = compute_stability_derivative(sub_sur.dCX_dq ,trans_sur.dCX_dq ,sup_sur.dCX_dq ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CX_r = compute_stability_derivative(sub_sur.dCX_dr ,trans_sur.dCX_dr ,sup_sur.dCX_dr ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CY_p = compute_stability_derivative(sub_sur.dCY_dp ,trans_sur.dCY_dp ,sup_sur.dCY_dp ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CY_q = compute_stability_derivative(sub_sur.dCY_dq ,trans_sur.dCY_dq ,sup_sur.dCY_dq ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CY_r = compute_stability_derivative(sub_sur.dCY_dr ,trans_sur.dCY_dr ,sup_sur.dCY_dr ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CZ_p = compute_stability_derivative(sub_sur.dCZ_dp ,trans_sur.dCZ_dp ,sup_sur.dCZ_dp ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CZ_q = compute_stability_derivative(sub_sur.dCZ_dq ,trans_sur.dCZ_dq ,sup_sur.dCZ_dq ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CZ_r = compute_stability_derivative(sub_sur.dCZ_dr ,trans_sur.dCZ_dr ,sup_sur.dCZ_dr ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CL_p = compute_stability_derivative(sub_sur.dCL_dp ,trans_sur.dCL_dp ,sup_sur.dCL_dp ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CL_q = compute_stability_derivative(sub_sur.dCL_dq ,trans_sur.dCL_dq ,sup_sur.dCL_dq ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CL_r = compute_stability_derivative(sub_sur.dCL_dr ,trans_sur.dCL_dr ,sup_sur.dCL_dr ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CM_p = compute_stability_derivative(sub_sur.dCM_dp ,trans_sur.dCM_dp ,sup_sur.dCM_dp ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CM_q = compute_stability_derivative(sub_sur.dCM_dq ,trans_sur.dCM_dq ,sup_sur.dCM_dq ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CM_r = compute_stability_derivative(sub_sur.dCM_dr ,trans_sur.dCM_dr ,sup_sur.dCM_dr ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CN_p = compute_stability_derivative(sub_sur.dCN_dp ,trans_sur.dCN_dp ,sup_sur.dCN_dp ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CN_q = compute_stability_derivative(sub_sur.dCN_dq ,trans_sur.dCN_dq ,sup_sur.dCN_dq ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CN_r = compute_stability_derivative(sub_sur.dCN_dr ,trans_sur.dCN_dr ,sup_sur.dCN_dr ,h_sub,h_sup,Mach)
if aerodynamics.elevator_flag:
conditions.static_stability.derivatives.Clift_delta_e = compute_stability_derivative(sub_sur.dClift_ddelta_e ,trans_sur.dClift_ddelta_e ,sup_sur.dClift_ddelta_e ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CX_delta_e = compute_stability_derivative(sub_sur.dCX_ddelta_e ,trans_sur.dCX_ddelta_e ,sup_sur.dCX_ddelta_e ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CY_delta_e = compute_stability_derivative(sub_sur.dCY_ddelta_e ,trans_sur.dCY_ddelta_e ,sup_sur.dCY_ddelta_e ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CZ_delta_e = compute_stability_derivative(sub_sur.dCZ_ddelta_e ,trans_sur.dCZ_ddelta_e ,sup_sur.dCZ_ddelta_e ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CL_delta_e = compute_stability_derivative(sub_sur.dCL_ddelta_e ,trans_sur.dCL_ddelta_e ,sup_sur.dCL_ddelta_e ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CM_delta_e = compute_stability_derivative(sub_sur.dCM_ddelta_e ,trans_sur.dCM_ddelta_e ,sup_sur.dCM_ddelta_e ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CN_delta_e = compute_stability_derivative(sub_sur.dCN_ddelta_e ,trans_sur.dCN_ddelta_e ,sup_sur.dCN_ddelta_e ,h_sub,h_sup,Mach)
if aerodynamics.aileron_flag:
conditions.static_stability.derivatives.Clift_delta_a = compute_stability_derivative(sub_sur.dClift_ddelta_a ,trans_sur.dClift_ddelta_a ,sup_sur.dClift_ddelta_a ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CX_delta_a = compute_stability_derivative(sub_sur.dCX_ddelta_a ,trans_sur.dCX_ddelta_a ,sup_sur.dCX_ddelta_a ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CY_delta_a = compute_stability_derivative(sub_sur.dCY_ddelta_a ,trans_sur.dCY_ddelta_a ,sup_sur.dCY_ddelta_a ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CZ_delta_a = compute_stability_derivative(sub_sur.dCZ_ddelta_a ,trans_sur.dCZ_ddelta_a ,sup_sur.dCZ_ddelta_a ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CL_delta_a = compute_stability_derivative(sub_sur.dCL_ddelta_a ,trans_sur.dCL_ddelta_a ,sup_sur.dCL_ddelta_a ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CM_delta_a = compute_stability_derivative(sub_sur.dCM_ddelta_a ,trans_sur.dCM_ddelta_a ,sup_sur.dCM_ddelta_a ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CN_delta_a = compute_stability_derivative(sub_sur.dCN_ddelta_a ,trans_sur.dCN_ddelta_a ,sup_sur.dCN_ddelta_a ,h_sub,h_sup,Mach)
if aerodynamics.rudder_flag:
conditions.static_stability.derivatives.Clift_delta_r = compute_stability_derivative(sub_sur.dClift_ddelta_r ,trans_sur.dClift_ddelta_r ,sup_sur.dClift_ddelta_r ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CX_delta_r = compute_stability_derivative(sub_sur.dCX_ddelta_r ,trans_sur.dCX_ddelta_r ,sup_sur.dCX_ddelta_r ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CY_delta_r = compute_stability_derivative(sub_sur.dCY_ddelta_r ,trans_sur.dCY_ddelta_r ,sup_sur.dCY_ddelta_r ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CZ_delta_r = compute_stability_derivative(sub_sur.dCZ_ddelta_r ,trans_sur.dCZ_ddelta_r ,sup_sur.dCZ_ddelta_r ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CL_delta_r = compute_stability_derivative(sub_sur.dCL_ddelta_r ,trans_sur.dCL_ddelta_r ,sup_sur.dCL_ddelta_r ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CM_delta_r = compute_stability_derivative(sub_sur.dCM_ddelta_r ,trans_sur.dCM_ddelta_r ,sup_sur.dCM_ddelta_r ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CN_delta_r = compute_stability_derivative(sub_sur.dCN_ddelta_r ,trans_sur.dCN_ddelta_r ,sup_sur.dCN_ddelta_r ,h_sub,h_sup,Mach)
if aerodynamics.flap_flag:
conditions.static_stability.derivatives.Clift_delta_f = compute_stability_derivative(sub_sur.dClift_ddelta_f ,trans_sur.dClift_ddelta_f ,sup_sur.dClift_ddelta_f ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CX_delta_f = compute_stability_derivative(sub_sur.dCX_ddelta_f ,trans_sur.dCX_ddelta_f ,sup_sur.dCX_ddelta_f ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CY_delta_f = compute_stability_derivative(sub_sur.dCY_ddelta_f ,trans_sur.dCY_ddelta_f ,sup_sur.dCY_ddelta_f ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CZ_delta_f = compute_stability_derivative(sub_sur.dCZ_ddelta_f ,trans_sur.dCZ_ddelta_f ,sup_sur.dCZ_ddelta_f ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CL_delta_f = compute_stability_derivative(sub_sur.dCL_ddelta_f ,trans_sur.dCL_ddelta_f ,sup_sur.dCL_ddelta_f ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CM_delta_f = compute_stability_derivative(sub_sur.dCM_ddelta_f ,trans_sur.dCM_ddelta_f ,sup_sur.dCM_ddelta_f ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CN_delta_f = compute_stability_derivative(sub_sur.dCN_ddelta_f ,trans_sur.dCN_ddelta_f ,sup_sur.dCN_ddelta_f ,h_sub,h_sup,Mach)
if aerodynamics.slat_flag:
conditions.static_stability.derivatives.Clift_delta_s = compute_stability_derivative(sub_sur.dClift_ddelta_s ,trans_sur.dClift_ddelta_s ,sup_sur.dClift_ddelta_s ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CX_delta_s = compute_stability_derivative(sub_sur.dCX_ddelta_s ,trans_sur.dCX_ddelta_s ,sup_sur.dCX_ddelta_s ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CY_delta_s = compute_stability_derivative(sub_sur.dCY_ddelta_s ,trans_sur.dCY_ddelta_s ,sup_sur.dCY_ddelta_s ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CZ_delta_s = compute_stability_derivative(sub_sur.dCZ_ddelta_s ,trans_sur.dCZ_ddelta_s ,sup_sur.dCZ_ddelta_s ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CL_delta_s = compute_stability_derivative(sub_sur.dCL_ddelta_s ,trans_sur.dCL_ddelta_s ,sup_sur.dCL_ddelta_s ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CM_delta_s = compute_stability_derivative(sub_sur.dCM_ddelta_s ,trans_sur.dCM_ddelta_s ,sup_sur.dCM_ddelta_s ,h_sub,h_sup,Mach)
conditions.static_stability.derivatives.CN_delta_s = compute_stability_derivative(sub_sur.dCN_ddelta_s ,trans_sur.dCN_ddelta_s ,sup_sur.dCN_ddelta_s ,h_sub,h_sup,Mach)
for wing in vehicle.wings:
inviscid_wing_lifts = compute_coefficient(sub_sur.Clift_wing_alpha[wing.tag],trans_sur.Clift_wing_alpha[wing.tag],sup_sur.Cdrag_wing_alpha[wing.tag] ,h_sub,h_sup,Mach,pts_alpha)
inviscid_wing_drags = compute_coefficient(sub_sur.Cdrag_wing_alpha[wing.tag],trans_sur.Cdrag_wing_alpha[wing.tag],sup_sur.Cdrag_wing_alpha[wing.tag] ,h_sub,h_sup,Mach,pts_alpha)
# Pack
conditions.aerodynamics.coefficients.lift.induced.inviscid_wings[wing.tag] = inviscid_wing_lifts
conditions.aerodynamics.coefficients.lift.compressible_wings[wing.tag] = inviscid_wing_lifts
conditions.aerodynamics.coefficients.drag.induced.inviscid_wings[wing.tag] = inviscid_wing_drags
conditions.aerodynamics.coefficients.lift.total = conditions.static_stability.coefficients.lift
conditions.aerodynamics.coefficients.drag.induced.inviscid = conditions.static_stability.coefficients.drag
return
[docs]
def evaluate_no_surrogate(state,settings,base_vehicle):
"""Evaluates forces and moments directly using VLM.
Assumptions:
The following stability derivatives are multiplied by correction
factors to match with literature/flight tests:
CY_beta multiplied by 2
CL_beta multiplied by -1
CL_p multiplied by -2
CM_q multiplied by 10
CN_p multiplied by -3
CN_r multiplied by 3
CL_delta_a multiplied by -1
CN_delta_a multiplied by -10
CLift_delta_e multiplied by 0.5
Source:
None
Args:
aerodynamics : VLM analysis [unitless]
state : flight conditions [unitless]
settings : VLM analysis settings [unitless]
vehicle : vehicle configuration [unitless]
Returns:
None
"""
# unpack
conditions = state.conditions
aerodynamics = state.analyses.aerodynamics
vehicle = aerodynamics.vehicle
Mach = state.conditions.freestream.mach_number
trim = aerodynamics.settings.trim_aircraft
for wing in vehicle.wings:
for control_surface in wing.control_surfaces:
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Aileron:
settings.aileron_flag = True
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Elevator:
settings.elevator_flag = True
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Rudder:
settings.rudder_flag = True
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Slat:
settings.slat_flag = True
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Flap:
settings.flap_flag = True
for i in range(len(Mach)):
for wing in vehicle.wings:
for control_surface in wing.control_surfaces:
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Aileron:
if trim == True:
control_surface.deflection = conditions.control_surfaces.aileron.deflection[i,0]
else:
conditions.control_surfaces.aileron.deflection[i, 0] = control_surface.deflection
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Elevator:
if trim == True:
control_surface.deflection = conditions.control_surfaces.elevator.deflection[i,0]
else:
conditions.control_surfaces.elevator.deflection[i, 0] = control_surface.deflection
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Rudder:
if trim == True:
control_surface.deflection = conditions.control_surfaces.rudder.deflection[i,0]
else:
conditions.control_surfaces.rudder.deflection[i, 0] = control_surface.deflection
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Slat:
conditions.control_surfaces.slat.deflection[i, 0] = control_surface.deflection
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Flap:
conditions.control_surfaces.flap.deflection[i, 0] = control_surface.deflection
VLM_results = VLM(conditions,settings,vehicle)
Clift = VLM_results.CLift
Cdrag = VLM_results.CDrag_induced
CX = VLM_results.CX
CY = VLM_results.CY
CZ = VLM_results.CZ
CL = VLM_results.CL
CM = VLM_results.CM
CN = VLM_results.CN
S_ref = VLM_results.S_ref
b_ref = VLM_results.b_ref
c_ref = VLM_results.c_ref
X_ref = VLM_results.X_ref
Y_ref = VLM_results.Y_ref
Z_ref = VLM_results.Z_ref
# Dimensionalize the lift and drag for each wing
conditions.aerodynamics.coefficients.lift.induced.inviscid_wings = VLM_results.CLift_wings
conditions.aerodynamics.coefficients.lift.compressible_wings = VLM_results.CLift_wings
conditions.aerodynamics.coefficients.drag.induced.inviscid_wings = VLM_results.CDrag_induced_wings
conditions.aerodynamics.coefficients.lift.induced.spanwise = VLM_results.sectional_CLift
conditions.aerodynamics.coefficients.drag.induced.spanwise = VLM_results.sectional_CDrag_induced
conditions.aerodynamics.coefficients.surface_pressure = VLM_results.CP
conditions.aerodynamics.coefficients.lift.total = Clift
conditions.aerodynamics.coefficients.drag.induced.inviscid = Cdrag
conditions.aerodynamics.angles.induced = VLM_results.alpha_induced
conditions.aerodynamics.chord_sections = VLM_results.chord_sections
conditions.aerodynamics.spanwise_stations = VLM_results.spanwise_stations
for wing in vehicle.wings:
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_wing(state,settings,wing)
for fuslage in vehicle.fuselages:
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_fuselage(state,settings,fuslage)
for boom in vehicle.booms:
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_fuselage(state,settings,boom)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_nacelle(state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_pylon(state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_total(state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.induced_drag(state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.cooling_drag(state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.compressibility_drag(state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.miscellaneous_drag(state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.spoiler_drag(state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.total_drag(state,settings,vehicle)
T_wind2inertial = conditions.frames.wind.transform_to_inertial
Cdrag_visc = state.conditions.aerodynamics.coefficients.drag.total
CX_visc = orientation_product(T_wind2inertial,Cdrag_visc)[:,0][:,None]
no_beta = np.all(conditions.aerodynamics.angles.beta == 0)
no_ail = np.all(conditions.control_surfaces.aileron.deflection == 0)
no_rud = np.all(conditions.control_surfaces.rudder.deflection == 0)
no_bank = np.all(conditions.aerodynamics.angles.phi == 0)
if no_beta and no_ail and no_rud and no_bank:
CY = CY * 0
conditions.static_stability.coefficients.lift[i, 0] = Clift[i, 0]
conditions.static_stability.coefficients.drag[i, 0] = Cdrag_visc[i, 0]
conditions.static_stability.coefficients.X[i, 0] = CX[i, 0]
conditions.static_stability.coefficients.Y[i, 0] = CY[i, 0]
conditions.static_stability.coefficients.Z[i, 0] = CZ[i, 0]
conditions.static_stability.coefficients.L[i, 0] = CL[i, 0]
conditions.static_stability.coefficients.M[i, 0] = CM[i, 0]
conditions.static_stability.coefficients.N[i, 0] = CN[i, 0]
# --------------------------------------------------------------------------------------------
# Unpack Pertubations
# --------------------------------------------------------------------------------------------
delta_angle = aerodynamics.training.angle_purtubation
delta_speed = aerodynamics.training.speed_purtubation
delta_rate = aerodynamics.training.rate_purtubation
delta_ctrl_surf = aerodynamics.training.control_surface_purtubation
# --------------------------------------------------------------------------------------------
# Equilibrium Condition
# --------------------------------------------------------------------------------------------
atmosphere = RCAIDE.Framework.Analyses.Atmospheric.US_Standard_1976()
atmo_data = atmosphere.compute_values(altitude = conditions.freestream.altitude)
equilibrium_conditions = RCAIDE.Framework.Mission.Common.Results()
equilibrium_conditions.energy = deepcopy(conditions.energy)
equilibrium_conditions.freestream.density[:,0] = atmo_data.density[0,0]
equilibrium_conditions.freestream.gravity[:,0] = conditions.freestream.gravity[0,0]
equilibrium_conditions.freestream.speed_of_sound[:,0] = atmo_data.speed_of_sound[0,0]
equilibrium_conditions.freestream.dynamic_viscosity[:,0] = atmo_data.dynamic_viscosity[0,0]
equilibrium_conditions.aerodynamics.angles.alpha[:,0] = 1E-12
equilibrium_conditions.freestream.temperature[:,0] = atmo_data.temperature[0,0]
equilibrium_conditions.freestream.velocity[:,0] = conditions.freestream.velocity[0,0]
equilibrium_conditions.frames.inertial.velocity_vector[:,0] = conditions.frames.inertial.velocity_vector[0,0]
equilibrium_conditions.freestream.mach_number = equilibrium_conditions.freestream.velocity/equilibrium_conditions.freestream.speed_of_sound
equilibrium_conditions.freestream.dynamic_pressure = 0.5 * equilibrium_conditions.freestream.density * (equilibrium_conditions.freestream.velocity ** 2)
equilibrium_conditions.freestream.reynolds_number = equilibrium_conditions.freestream.density * equilibrium_conditions.freestream.velocity * wing.chords.mean_aerodynamic/ equilibrium_conditions.freestream.dynamic_viscosity
VLM_results = VLM(equilibrium_conditions,settings,vehicle)
Clift_0 = VLM_results.CLift
Cdrag_0 = VLM_results.CDrag_induced
CX_0 = VLM_results.CX
CY_0 = VLM_results.CY
CZ_0 = VLM_results.CZ
CL_0 = VLM_results.CL
CM_0 = VLM_results.CM
CN_0 = VLM_results.CN
# Dimensionalize the lift and drag for each wing
equilibrium_conditions.aerodynamics.coefficients.lift.induced.inviscid_wings = VLM_results.CLift_wings
equilibrium_conditions.aerodynamics.coefficients.lift.compressible_wings = VLM_results.CLift_wings
equilibrium_conditions.aerodynamics.coefficients.drag.induced.inviscid_wings = VLM_results.CDrag_induced_wings
equilibrium_conditions.aerodynamics.coefficients.lift.total = Clift_0
equilibrium_conditions.aerodynamics.coefficients.drag.induced.inviscid = Cdrag_0
equilibrium_state = RCAIDE.Framework.Mission.Common.State()
equilibrium_state.conditions = equilibrium_conditions
equilibrium_segment = RCAIDE.Framework.Mission.Segments.Single_Point.Set_Speed_Set_Altitude()
equilibrium_segment.conditions = equilibrium_conditions
equilibrium_segment.state.conditions = equilibrium_conditions
orientation(equilibrium_segment)
orientations(equilibrium_segment)
for wing in vehicle.wings:
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_wing(equilibrium_state,settings,wing)
for fuslage in vehicle.fuselages:
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_fuselage(equilibrium_state,settings,fuslage)
for boom in vehicle.booms:
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_fuselage(equilibrium_state,settings,boom)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_nacelle(equilibrium_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_pylon(equilibrium_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_total(equilibrium_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.induced_drag(equilibrium_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.cooling_drag(equilibrium_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.compressibility_drag(equilibrium_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.miscellaneous_drag(equilibrium_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.spoiler_drag(equilibrium_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.total_drag(equilibrium_state,settings,vehicle)
T_wind2inertial = equilibrium_conditions.frames.wind.transform_to_inertial
Cdrag_0 = equilibrium_state.conditions.aerodynamics.coefficients.drag.total
CX_0 = orientation_product(T_wind2inertial,Cdrag_0)[:,0][:,None]
# --------------------------------------------------------------------------------------------
# Alpha Purtubation
# --------------------------------------------------------------------------------------------
perturbation_state = deepcopy(equilibrium_state)
pertubation_conditions = deepcopy(equilibrium_conditions)
pertubation_conditions.aerodynamics.angles.alpha += delta_angle
VLM_results = VLM(pertubation_conditions,settings,vehicle)
Clift_alpha_prime = VLM_results.CLift
Cdrag_alpha_prime = VLM_results.CDrag_induced
CY_alpha_prime = VLM_results.CY
CZ_alpha_prime = VLM_results.CZ
CL_alpha_prime = VLM_results.CL
CM_alpha_prime = VLM_results.CM
CN_alpha_prime = VLM_results.CN
pertubation_conditions.aerodynamics.coefficients.lift.induced.inviscid_wings = VLM_results.CLift_wings
pertubation_conditions.aerodynamics.coefficients.lift.compressible_wings = VLM_results.CLift_wings
pertubation_conditions.aerodynamics.coefficients.drag.induced.inviscid_wings = VLM_results.CDrag_induced_wings
pertubation_conditions.aerodynamics.coefficients.lift.total = Clift_alpha_prime
pertubation_conditions.aerodynamics.coefficients.drag.induced.inviscid = Cdrag_alpha_prime
perturbation_state = RCAIDE.Framework.Mission.Common.State()
perturbation_state.conditions = pertubation_conditions
perturbation_state = RCAIDE.Framework.Mission.Segments.Single_Point.Set_Speed_Set_Altitude()
perturbation_state.conditions = pertubation_conditions
perturbation_state.state.conditions = pertubation_conditions
orientation(perturbation_state)
orientations(perturbation_state)
for wing in vehicle.wings:
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_wing(perturbation_state,settings,wing)
for fuslage in vehicle.fuselages:
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_fuselage(perturbation_state,settings,fuslage)
for boom in vehicle.booms:
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_fuselage(perturbation_state,settings,boom)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_nacelle(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_pylon(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_total(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.induced_drag(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.cooling_drag(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.compressibility_drag(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.miscellaneous_drag(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.spoiler_drag(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.total_drag(perturbation_state,settings,vehicle)
T_wind2inertial = pertubation_conditions.frames.wind.transform_to_inertial
Cdrag_visc_prime = perturbation_state.conditions.aerodynamics.coefficients.drag.total
CX_visc_prime = orientation_product(T_wind2inertial,Cdrag_visc_prime)[:,0][:,None]
conditions.static_stability.derivatives.Clift_alpha = (Clift_alpha_prime - Clift_0) / (delta_angle)
conditions.static_stability.derivatives.Cdrag_alpha = (Cdrag_alpha_prime - Cdrag_0) / (delta_angle)
conditions.static_stability.derivatives.CX_alpha = (CX_visc_prime - CX_0) / (delta_angle)
conditions.static_stability.derivatives.CY_alpha = (CY_alpha_prime - CY_0) / (delta_angle)
conditions.static_stability.derivatives.CZ_alpha = (CZ_alpha_prime - CZ_0) / (delta_angle)
conditions.static_stability.derivatives.CL_alpha = (CL_alpha_prime - CL_0) / (delta_angle)
conditions.static_stability.derivatives.CM_alpha = (CM_alpha_prime - CM_0) / (delta_angle)
conditions.static_stability.derivatives.CN_alpha = (CN_alpha_prime - CN_0) / (delta_angle)
# --------------------------------------------------------------------------------------------
# Neutral Point - CG Purtubation
# --------------------------------------------------------------------------------------------
perturbation_state = deepcopy(equilibrium_state)
pertubation_conditions = deepcopy(equilibrium_conditions)
pertubation_conditions.aerodynamics.angles.alpha += delta_angle
vehicle_shifted_CG = deepcopy(vehicle)
delta_cg = 0.1
vehicle_shifted_CG.mass_properties.center_of_gravity[0][0] +=delta_cg
VLM_results = VLM(pertubation_conditions,settings,vehicle_shifted_CG)
CM_alpha_cg_prime = VLM_results.CM
dCM_dalpha_cg = (CM_alpha_cg_prime - CM_0) / (delta_angle)
dCM_dalpha = (CM_alpha_prime - CM_0) / (delta_angle)
m = (dCM_dalpha_cg[0] - dCM_dalpha[0]) /delta_cg
b = dCM_dalpha_cg[0] - (m * vehicle_shifted_CG.mass_properties.center_of_gravity[0][0])
NP = -b / m
conditions.static_stability.neutral_point[0,0] = NP
vehicle.mass_properties.neutral_point = NP
# --------------------------------------------------------------------------------------------
# Beta Purtubation
# --------------------------------------------------------------------------------------------
pertubation_conditions = deepcopy(equilibrium_conditions)
pertubation_conditions.aerodynamics.angles.beta += delta_angle
VLM_results = VLM(pertubation_conditions,settings,vehicle)
Clift_beta_prime = VLM_results.CLift
Cdrag_beta_prime = VLM_results.CDrag_induced
CX_beta_prime = VLM_results.CX
CY_beta_prime = VLM_results.CY
CZ_beta_prime = VLM_results.CZ
CL_beta_prime = VLM_results.CL
CM_beta_prime = VLM_results.CM
CN_beta_prime = VLM_results.CN
conditions.static_stability.derivatives.Clift_beta = (Clift_beta_prime - Clift_0) / (delta_angle)
conditions.static_stability.derivatives.Cdrag_beta = (Cdrag_beta_prime - Cdrag_0) / (delta_angle)
conditions.static_stability.derivatives.CX_beta = (CX_beta_prime - CX_0) / (delta_angle)
conditions.static_stability.derivatives.CY_beta = 2*(CY_beta_prime - CY_0) / (delta_angle)
conditions.static_stability.derivatives.CZ_beta = (CZ_beta_prime - CZ_0) / (delta_angle)
conditions.static_stability.derivatives.CL_beta = -(CL_beta_prime - CL_0) / (delta_angle)
conditions.static_stability.derivatives.CM_beta = (CM_beta_prime - CM_0) / (delta_angle)
conditions.static_stability.derivatives.CN_beta = (CN_beta_prime - CN_0) / (delta_angle)
# --------------------------------------------------------------------------------------------
# U-Velocity Pertubation
# --------------------------------------------------------------------------------------------
perturbation_state = deepcopy(equilibrium_state)
pertubation_conditions = deepcopy(equilibrium_conditions)
pertubation_conditions.frames.inertial.velocity_vector[:,0] += delta_speed
pertubation_conditions.freestream.velocity [:,0] += delta_speed
pertubation_conditions.freestream.mach_number = np.linalg.norm(pertubation_conditions.frames.inertial.velocity_vector, axis=1)[:,None] / equilibrium_conditions.freestream.speed_of_sound
pertubation_conditions.freestream.reynolds_number = pertubation_conditions.freestream.density * pertubation_conditions.freestream.velocity * wing.chords.mean_aerodynamic/equilibrium_conditions.freestream.dynamic_viscosity
pertubation_conditions.freestream.dynamic_pressure = 0.5 * pertubation_conditions.freestream.density * np.sum( pertubation_conditions.freestream.velocity**2, axis=1)[:,None]
VLM_results = VLM(pertubation_conditions,settings,vehicle)
Clift_u_prime = VLM_results.CLift
Cdrag_u_prime = VLM_results.CDrag_induced
CX_u_prime = VLM_results.CX
CY_u_prime = VLM_results.CY
CZ_u_prime = VLM_results.CZ
CL_u_prime = VLM_results.CL
CM_u_prime = VLM_results.CM
CN_u_prime = VLM_results.CN
# Dimensionalize the lift and drag for each wing
for wing in vehicle.wings:
pertubation_conditions.aerodynamics.coefficients.lift.induced.inviscid_wings = VLM_results.CLift_wings
pertubation_conditions.aerodynamics.coefficients.lift.compressible_wings = VLM_results.CLift_wings
pertubation_conditions.aerodynamics.coefficients.drag.induced.inviscid_wings = VLM_results.CDrag_induced_wings
pertubation_conditions.aerodynamics.coefficients.lift.total = Clift_u_prime
pertubation_conditions.aerodynamics.coefficients.drag.induced.inviscid = Cdrag_u_prime
perturbation_state = RCAIDE.Framework.Mission.Common.State()
perturbation_state.conditions = pertubation_conditions
perturbation_state = RCAIDE.Framework.Mission.Segments.Single_Point.Set_Speed_Set_Altitude()
perturbation_state.conditions = pertubation_conditions
perturbation_state.state.conditions = pertubation_conditions
orientation(perturbation_state)
orientations(perturbation_state)
for wing in vehicle.wings:
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_wing(perturbation_state,settings,wing)
for fuslage in vehicle.fuselages:
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_fuselage(perturbation_state,settings,fuslage)
for boom in vehicle.booms:
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_fuselage(perturbation_state,settings,boom)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_nacelle(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_pylon(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_total(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.induced_drag(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.cooling_drag(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.compressibility_drag(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.miscellaneous_drag(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.spoiler_drag(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.total_drag(perturbation_state,settings,vehicle)
T_wind2inertial = pertubation_conditions.frames.wind.transform_to_inertial
Cdrag_visc_prime = perturbation_state.conditions.aerodynamics.coefficients.drag.total
CX_visc_prime = orientation_product(T_wind2inertial,Cdrag_visc_prime)[:,0][:,None]
conditions.static_stability.derivatives.Clift_u = (Clift_u_prime - Clift_0) / (delta_speed)
conditions.static_stability.derivatives.Cdrag_u = (Cdrag_visc_prime - Cdrag_0) / (delta_speed)
conditions.static_stability.derivatives.CX_u = (CX_visc_prime - CX_0) / (delta_speed)
conditions.static_stability.derivatives.CY_u = (CY_u_prime - CY_0) / (delta_speed)
conditions.static_stability.derivatives.CZ_u = (CZ_u_prime - CZ_0) / (delta_speed)
conditions.static_stability.derivatives.CL_u = (CL_u_prime - CL_0) / (delta_speed)
conditions.static_stability.derivatives.CM_u = (CM_u_prime - CM_0) / (delta_speed)
conditions.static_stability.derivatives.CN_u = (CN_u_prime - CN_0) / (delta_speed)
# --------------------------------------------------------------------------------------------
# V-Velocity Pertubation
# -------------------------------------------------------------------------------------------
pertubation_conditions = deepcopy(equilibrium_conditions)
pertubation_conditions.frames.inertial.velocity_vector[:,1] += delta_speed
pertubation_conditions.freestream.velocity = np.linalg.norm(pertubation_conditions.frames.inertial.velocity_vector, axis=1)[:,None]
pertubation_conditions.freestream.mach_number = pertubation_conditions.freestream.velocity/ pertubation_conditions.freestream.speed_of_sound
pertubation_conditions.freestream.reynolds_number = pertubation_conditions.freestream.density * pertubation_conditions.freestream.velocity / pertubation_conditions.freestream.dynamic_viscosity
pertubation_conditions.freestream.dynamic_pressure = 0.5 * pertubation_conditions.freestream.density * np.sum( pertubation_conditions.freestream.velocity**2, axis=1)[:,None]
VLM_results = VLM(pertubation_conditions,settings,vehicle)
Clift_v_prime = VLM_results.CLift
Cdrag_v_prime = VLM_results.CDrag_induced
CX_v_prime = VLM_results.CX
CY_v_prime = VLM_results.CY
CZ_v_prime = VLM_results.CZ
CL_v_prime = VLM_results.CL
CM_v_prime = VLM_results.CM
CN_v_prime = VLM_results.CN
conditions.static_stability.derivatives.Clift_v = (Clift_v_prime - Clift_0) / (delta_speed)
conditions.static_stability.derivatives.Cdrag_v = (Cdrag_v_prime - Cdrag_0) / (delta_speed)
conditions.static_stability.derivatives.CX_v = (CX_v_prime - CX_0) / (delta_speed)
conditions.static_stability.derivatives.CY_v = (CY_v_prime - CY_0) / (delta_speed)
conditions.static_stability.derivatives.CZ_v = (CZ_v_prime - CZ_0) / (delta_speed)
conditions.static_stability.derivatives.CL_v = (CL_v_prime - CL_0) / (delta_speed)
conditions.static_stability.derivatives.CM_v = (CM_v_prime - CM_0) / (delta_speed)
conditions.static_stability.derivatives.CN_v = (CN_v_prime - CN_0) / (delta_speed)
# --------------------------------------------------------------------------------------------
# W-Velocity Pertubation
# --------------------------------------------------------------------------------------------
pertubation_conditions = deepcopy(equilibrium_conditions)
pertubation_conditions.frames.inertial.velocity_vector[:,2] += delta_speed
pertubation_conditions.freestream.velocity = np.linalg.norm(pertubation_conditions.frames.inertial.velocity_vector, axis=1)[:,None]
pertubation_conditions.freestream.mach_number =pertubation_conditions.freestream.velocity / pertubation_conditions.freestream.speed_of_sound
pertubation_conditions.freestream.reynolds_number = pertubation_conditions.freestream.density * pertubation_conditions.freestream.velocity / pertubation_conditions.freestream.dynamic_viscosity
pertubation_conditions.freestream.dynamic_pressure = 0.5 * pertubation_conditions.freestream.density * np.sum( pertubation_conditions.freestream.velocity**2, axis=1)[:,None]
VLM_results = VLM(pertubation_conditions,settings,vehicle)
Clift_w_prime = VLM_results.CLift
Cdrag_w_prime = VLM_results.CDrag_induced
CX_w_prime = VLM_results.CX
CY_w_prime = VLM_results.CY
CZ_w_prime = VLM_results.CZ
CL_w_prime = VLM_results.CL
CM_w_prime = VLM_results.CM
CN_w_prime = VLM_results.CN
conditions.static_stability.derivatives.Clift_w = (Clift_w_prime - Clift_0) / (delta_speed)
conditions.static_stability.derivatives.Cdrag_w = (Cdrag_w_prime - Cdrag_0) / (delta_speed)
conditions.static_stability.derivatives.CX_w = (CX_w_prime - CX_0) / (delta_speed)
conditions.static_stability.derivatives.CY_w = (CY_w_prime - CY_0) / (delta_speed)
conditions.static_stability.derivatives.CZ_w = (CZ_w_prime - CZ_0) / (delta_speed)
conditions.static_stability.derivatives.CL_w = (CL_w_prime - CL_0) / (delta_speed)
conditions.static_stability.derivatives.CM_w = (CM_w_prime - CM_0) / (delta_speed)
conditions.static_stability.derivatives.CN_w = (CN_w_prime - CN_0) / (delta_speed)
# --------------------------------------------------------------------------------------------
# Roll Rate (p) Purtubation
# --------------------------------------------------------------------------------------------
pertubation_conditions = deepcopy(equilibrium_conditions)
pertubation_conditions.static_stability.roll_rate[:,0] += delta_rate
VLM_results = VLM(pertubation_conditions,settings,vehicle)
Clift_p_prime = VLM_results.CLift
Cdrag_p_prime = VLM_results.CDrag_induced
CX_p_prime = VLM_results.CX
CY_p_prime = VLM_results.CY
CZ_p_prime = VLM_results.CZ
CL_p_prime = VLM_results.CL
CM_p_prime = VLM_results.CM
CN_p_prime = VLM_results.CN
conditions.static_stability.derivatives.Clift_p = (Clift_p_prime - Clift_0) / (delta_rate)
conditions.static_stability.derivatives.Cdrag_p = (Cdrag_p_prime - Cdrag_0) / (delta_rate)
conditions.static_stability.derivatives.CX_p = (CX_p_prime - CX_0) / (delta_rate)
conditions.static_stability.derivatives.CY_p = (CY_p_prime - CY_0) / (delta_rate)
conditions.static_stability.derivatives.CZ_p = (CZ_p_prime - CZ_0) / (delta_rate)
conditions.static_stability.derivatives.CL_p = -2*(CL_p_prime - CL_0) / (delta_rate)
conditions.static_stability.derivatives.CM_p = (CM_p_prime - CM_0) / (delta_rate)
conditions.static_stability.derivatives.CN_p = -3*(CN_p_prime - CN_0) / (delta_rate)
# ---------------------------------------------------------------------------------------------------
# Pitch Rate (q) Purtubation
# ---------------------------------------------------------------------------------------------------
perturbation_state = deepcopy(equilibrium_state)
pertubation_conditions = deepcopy(equilibrium_conditions)
pertubation_conditions.static_stability.pitch_rate[:,0] += delta_rate
VLM_results = VLM(pertubation_conditions,settings,vehicle)
Clift_q_prime = VLM_results.CLift
Cdrag_q_prime = VLM_results.CDrag_induced
CX_q_prime = VLM_results.CX
CY_q_prime = VLM_results.CY
CZ_q_prime = VLM_results.CZ
CL_q_prime = VLM_results.CL
CM_q_prime = VLM_results.CM
CN_q_prime = VLM_results.CN
# Dimensionalize the lift and drag for each wing
pertubation_conditions.aerodynamics.coefficients.lift.induced.inviscid_wings = VLM_results.CLift_wings
pertubation_conditions.aerodynamics.coefficients.lift.compressible_wings = VLM_results.CLift_wings
pertubation_conditions.aerodynamics.coefficients.drag.induced.inviscid_wings = VLM_results.CDrag_induced_wings
pertubation_conditions.aerodynamics.coefficients.lift.total = Clift_q_prime
pertubation_conditions.aerodynamics.coefficients.drag.induced.inviscid = Cdrag_q_prime
perturbation_state = RCAIDE.Framework.Mission.Common.State()
perturbation_state.conditions = pertubation_conditions
perturbation_state = RCAIDE.Framework.Mission.Segments.Single_Point.Set_Speed_Set_Altitude()
perturbation_state.conditions = pertubation_conditions
perturbation_state.state.conditions = pertubation_conditions
orientation(perturbation_state)
orientations(perturbation_state)
for wing in vehicle.wings:
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_wing(perturbation_state,settings,wing)
for fuslage in vehicle.fuselages:
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_fuselage(perturbation_state,settings,fuslage)
for boom in vehicle.booms:
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_fuselage(perturbation_state,settings,boom)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_nacelle(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_pylon(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_total(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.induced_drag(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.cooling_drag(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.compressibility_drag(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.miscellaneous_drag(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.spoiler_drag(perturbation_state,settings,vehicle)
RCAIDE.Library.Methods.Aerodynamics.Common.Drag.total_drag(perturbation_state,settings,vehicle)
T_wind2inertial = pertubation_conditions.frames.wind.transform_to_inertial
Cdrag_visc_prime = perturbation_state.conditions.aerodynamics.coefficients.drag.total
CX_visc_prime = orientation_product(T_wind2inertial,Cdrag_visc_prime)[:,0][:,None]
conditions.static_stability.derivatives.Clift_q = (Clift_q_prime - Clift_0) / (delta_rate)
conditions.static_stability.derivatives.Cdrag_q = (Cdrag_q_prime - Cdrag_0) / (delta_rate)
conditions.static_stability.derivatives.CX_q = (CX_visc_prime - CX_0)/ (delta_rate)
conditions.static_stability.derivatives.CY_q = (CY_q_prime - CY_0) / (delta_rate)
conditions.static_stability.derivatives.CZ_q = (CZ_q_prime - CZ_0) / (delta_rate)
conditions.static_stability.derivatives.CL_q = (CL_q_prime - CL_0) / (delta_rate)
conditions.static_stability.derivatives.CM_q = 10*(CM_q_prime - CM_0) / (delta_rate)
conditions.static_stability.derivatives.CN_q = (CN_q_prime - CN_0)/ (delta_rate)
# ---------------------------------------------------------------------------------------------------
# Yaw Rate (r) Purtubation
# ---------------------------------------------------------------------------------------------------
pertubation_conditions = deepcopy(equilibrium_conditions)
pertubation_conditions.static_stability.yaw_rate[:,0] += delta_rate
VLM_results = VLM(pertubation_conditions,settings,vehicle)
Clift_r_prime = VLM_results.CLift
Cdrag_r_prime = VLM_results.CDrag_induced
CX_r_prime = VLM_results.CX
CY_r_prime = VLM_results.CY
CZ_r_prime = VLM_results.CZ
CL_r_prime = VLM_results.CL
CM_r_prime = VLM_results.CM
CN_r_prime = VLM_results.CN
conditions.static_stability.derivatives.Clift_r = (Clift_r_prime - Clift_0) / (delta_rate)
conditions.static_stability.derivatives.Cdrag_r = (Cdrag_r_prime - Cdrag_0) / (delta_rate)
conditions.static_stability.derivatives.CX_r = (CX_r_prime - CX_0) / (delta_rate)
conditions.static_stability.derivatives.CY_r = (CY_r_prime - CY_0) / (delta_rate)
conditions.static_stability.derivatives.CZ_r = (CZ_r_prime - CZ_0) / (delta_rate)
conditions.static_stability.derivatives.CL_r = (CL_r_prime - CL_0) / (delta_rate)
conditions.static_stability.derivatives.CM_r = (CM_r_prime - CM_0) / (delta_rate)
conditions.static_stability.derivatives.CN_r = 3*(CN_r_prime - CN_0) / (delta_rate)
# only compute derivative if control surface exists
if settings.aileron_flag:
pertubation_conditions = deepcopy(equilibrium_conditions)
for wing in vehicle.wings:
for control_surface in wing.control_surfaces:
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Aileron:
vehicle.wings[wing.tag].control_surfaces.aileron.deflection = delta_ctrl_surf
VLM_results = VLM(pertubation_conditions,settings,vehicle)
Clift_res = VLM_results.CLift
Cdrag_res = VLM_results.CDrag_induced
CX_res = VLM_results.CX
CY_res = VLM_results.CY
CZ_res = VLM_results.CZ
CL_res = VLM_results.CL
CM_res = VLM_results.CM
CN_res = VLM_results.CN
vehicle.wings[wing.tag].control_surfaces.aileron.deflection = 0
Clift_delta_a_prime = Clift_res
Cdrag_delta_a_prime = Cdrag_res
CX_delta_a_prime = CX_res
CY_delta_a_prime = CY_res
CZ_delta_a_prime = CZ_res
CL_delta_a_prime = CL_res
CM_delta_a_prime = CM_res
CN_delta_a_prime = CN_res
dClift_ddelta_a = (Clift_delta_a_prime - Clift_0) / (delta_ctrl_surf)
dCdrag_ddelta_a = (Cdrag_delta_a_prime - Cdrag_0) / (delta_ctrl_surf)
dCX_ddelta_a = (CX_delta_a_prime - CX_0) / (delta_ctrl_surf)
dCY_ddelta_a = (CY_delta_a_prime - CY_0) / (delta_ctrl_surf)
dCZ_ddelta_a = (CZ_delta_a_prime - CZ_0) / (delta_ctrl_surf)
dCL_ddelta_a = -(CL_delta_a_prime - CL_0) / (delta_ctrl_surf)
dCM_ddelta_a = (CM_delta_a_prime - CM_0) / (delta_ctrl_surf)
dCN_ddelta_a = -10*(CN_delta_a_prime - CN_0) / (delta_ctrl_surf)
conditions.static_stability.derivatives.Clift_delta_a = dClift_ddelta_a
conditions.static_stability.derivatives.Cdrag_delta_a = dCdrag_ddelta_a
conditions.static_stability.derivatives.CX_delta_a = dCX_ddelta_a
conditions.static_stability.derivatives.CY_delta_a = dCY_ddelta_a
conditions.static_stability.derivatives.CZ_delta_a = dCZ_ddelta_a
conditions.static_stability.derivatives.CL_delta_a = dCL_ddelta_a
conditions.static_stability.derivatives.CM_delta_a = dCM_ddelta_a
conditions.static_stability.derivatives.CN_delta_a = dCN_ddelta_a
if settings.elevator_flag:
pertubation_conditions = deepcopy(equilibrium_conditions)
for wing in vehicle.wings:
for control_surface in wing.control_surfaces:
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Elevator:
vehicle.wings[wing.tag].control_surfaces.elevator.deflection = delta_ctrl_surf
VLM_results = VLM(pertubation_conditions,settings,vehicle)
Clift_res = VLM_results.CLift
Cdrag_res = VLM_results.CDrag_induced
CX_res = VLM_results.CX
CY_res = VLM_results.CY
CZ_res = VLM_results.CZ
CL_res = VLM_results.CL
CM_res = VLM_results.CM
CN_res = VLM_results.CN
vehicle.wings[wing.tag].control_surfaces.elevator.deflection = 0
Clift_delta_e_prime = Clift_res
Cdrag_delta_e_prime = Cdrag_res
CX_delta_e_prime = CX_res
CY_delta_e_prime = CY_res
CZ_delta_e_prime = CZ_res
CL_delta_e_prime = CL_res
CM_delta_e_prime = CM_res
CN_delta_e_prime = CN_res
dClift_ddelta_e = 0.5*(Clift_delta_e_prime - Clift_0) / (delta_ctrl_surf)
dCdrag_ddelta_e = (Cdrag_delta_e_prime - Cdrag_0) / (delta_ctrl_surf)
dCX_ddelta_e = (CX_delta_e_prime - CX_0) / (delta_ctrl_surf)
dCY_ddelta_e = (CY_delta_e_prime - CY_0) / (delta_ctrl_surf)
dCZ_ddelta_e = (CZ_delta_e_prime - CZ_0) / (delta_ctrl_surf)
dCL_ddelta_e = (CL_delta_e_prime - CL_0) / (delta_ctrl_surf)
dCM_ddelta_e = (CM_delta_e_prime - CM_0) / (delta_ctrl_surf)
dCN_ddelta_e = (CN_delta_e_prime - CN_0) / (delta_ctrl_surf)
conditions.static_stability.derivatives.Clift_delta_e = dClift_ddelta_e
conditions.static_stability.derivatives.Cdrag_delta_e = dCdrag_ddelta_e
conditions.static_stability.derivatives.CX_delta_e = dCX_ddelta_e
conditions.static_stability.derivatives.CY_delta_e = dCY_ddelta_e
conditions.static_stability.derivatives.CZ_delta_e = dCZ_ddelta_e
conditions.static_stability.derivatives.CL_delta_e = dCL_ddelta_e
conditions.static_stability.derivatives.CM_delta_e = dCM_ddelta_e
conditions.static_stability.derivatives.CN_delta_e = dCN_ddelta_e
if settings.rudder_flag:
pertubation_conditions = deepcopy(equilibrium_conditions)
for wing in vehicle.wings:
for control_surface in wing.control_surfaces:
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Rudder:
vehicle.wings[wing.tag].control_surfaces.rudder.deflection = delta_ctrl_surf
VLM_results = VLM(pertubation_conditions,settings,vehicle)
Clift_res = VLM_results.CLift
Cdrag_res = VLM_results.CDrag_induced
CX_res = VLM_results.CX
CY_res = VLM_results.CY
CZ_res = VLM_results.CZ
CL_res = VLM_results.CL
CM_res = VLM_results.CM
CN_res = VLM_results.CN
vehicle.wings[wing.tag].control_surfaces.rudder.deflection = 0
Clift_delta_r_prime = Clift_res
Cdrag_delta_r_prime = Cdrag_res
CX_delta_r_prime = CX_res
CY_delta_r_prime = CY_res
CZ_delta_r_prime = CZ_res
CL_delta_r_prime = CL_res
CM_delta_r_prime = CM_res
CN_delta_r_prime = CN_res
dClift_ddelta_r = (Clift_delta_r_prime - Clift_0) / (delta_ctrl_surf)
dCdrag_ddelta_r = (Cdrag_delta_r_prime - Cdrag_0) / (delta_ctrl_surf)
dCX_ddelta_r = (CX_delta_r_prime - CX_0) / (delta_ctrl_surf)
dCY_ddelta_r = (CY_delta_r_prime - CY_0) / (delta_ctrl_surf)
dCZ_ddelta_r = (CZ_delta_r_prime - CZ_0) / (delta_ctrl_surf)
dCL_ddelta_r = (CL_delta_r_prime - CL_0) / (delta_ctrl_surf)
dCM_ddelta_r = (CM_delta_r_prime - CM_0) / (delta_ctrl_surf)
dCN_ddelta_r = (CN_delta_r_prime - CN_0) / (delta_ctrl_surf)
conditions.static_stability.derivatives.Clift_delta_r = dClift_ddelta_r
conditions.static_stability.derivatives.Cdrag_delta_r = dCdrag_ddelta_r
conditions.static_stability.derivatives.CX_delta_r = dCX_ddelta_r
conditions.static_stability.derivatives.CY_delta_r = dCY_ddelta_r
conditions.static_stability.derivatives.CZ_delta_r = dCZ_ddelta_r
conditions.static_stability.derivatives.CL_delta_r = dCL_ddelta_r
conditions.static_stability.derivatives.CM_delta_r = dCM_ddelta_r
conditions.static_stability.derivatives.CN_delta_r = dCN_ddelta_r
if settings.flap_flag:
pertubation_conditions = deepcopy(equilibrium_conditions)
for wing in vehicle.wings:
for control_surface in wing.control_surfaces:
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Flap:
vehicle.wings[wing.tag].control_surfaces.flap.deflection = delta_ctrl_surf
VLM_results = VLM(pertubation_conditions,settings,vehicle)
Clift_res = VLM_results.CLift
Cdrag_res = VLM_results.CDrag_induced
CX_res = VLM_results.CX
CY_res = VLM_results.CY
CZ_res = VLM_results.CZ
CL_res = VLM_results.CL
CM_res = VLM_results.CM
CN_res = VLM_results.CN
vehicle.wings[wing.tag].control_surfaces.flap.deflection = 0
Clift_delta_f_prime = Clift_res
Cdrag_delta_f_prime = Cdrag_res
CX_delta_f_prime = CX_res
CY_delta_f_prime = CY_res
CZ_delta_f_prime = CZ_res
CL_delta_f_prime = CL_res
CM_delta_f_prime = CM_res
CN_delta_f_prime = CN_res
dClift_ddelta_f = (Clift_delta_f_prime - Clift_0) / (delta_ctrl_surf)
dCdrag_ddelta_f = (Cdrag_delta_f_prime - Cdrag_0) / (delta_ctrl_surf)
dCX_ddelta_f = (CX_delta_f_prime - CX_0) / (delta_ctrl_surf)
dCY_ddelta_f = (CY_delta_f_prime - CY_0) / (delta_ctrl_surf)
dCZ_ddelta_f = (CZ_delta_f_prime - CZ_0) / (delta_ctrl_surf)
dCL_ddelta_f = (CL_delta_f_prime - CL_0) / (delta_ctrl_surf)
dCM_ddelta_f = (CM_delta_f_prime - CM_0) / (delta_ctrl_surf)
dCN_ddelta_f = (CN_delta_f_prime - CN_0) / (delta_ctrl_surf)
conditions.static_stability.derivatives.Clift_delta_f = dClift_ddelta_f
conditions.static_stability.derivatives.Clift_delta_f = dCdrag_ddelta_f
conditions.static_stability.derivatives.CX_delta_f = dCX_ddelta_f
conditions.static_stability.derivatives.CY_delta_f = dCY_ddelta_f
conditions.static_stability.derivatives.CZ_delta_f = dCZ_ddelta_f
conditions.static_stability.derivatives.CL_delta_f = dCL_ddelta_f
conditions.static_stability.derivatives.CM_delta_f = dCM_ddelta_f
conditions.static_stability.derivatives.CN_delta_f = dCN_ddelta_f
if settings.slat_flag:
pertubation_conditions = deepcopy(equilibrium_conditions)
for wing in vehicle.wings:
for control_surface in wing.control_surfaces:
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Slat:
vehicle.wings[wing.tag].control_surfaces.slat.deflection = delta_ctrl_surf
VLM_results = VLM(pertubation_conditions,settings,vehicle)
Clift_res = VLM_results.CLift
Cdrag_res = VLM_results.CDrag_induced
CX_res = VLM_results.CX
CY_res = VLM_results.CY
CZ_res = VLM_results.CZ
CL_res = VLM_results.CL
CM_res = VLM_results.CM
CN_res = VLM_results.CN
vehicle.wings[wing.tag].control_surfaces.slat.deflection = 0
Clift_delta_s_prime = Clift_res
Cdrag_delta_s_prime = Cdrag_res
CX_delta_s_prime = CX_res
CY_delta_s_prime = CY_res
CZ_delta_s_prime = CZ_res
CL_delta_s_prime = CL_res
CM_delta_s_prime = CM_res
CN_delta_s_prime = CN_res
dClift_ddelta_s = (Clift_delta_s_prime - Clift_0) / (delta_ctrl_surf)
dCdrag_ddelta_s = (Cdrag_delta_s_prime - Cdrag_0) / (delta_ctrl_surf)
dCX_ddelta_s = (CX_delta_s_prime - CX_0) / (delta_ctrl_surf)
dCY_ddelta_s = (CY_delta_s_prime - CY_0) / (delta_ctrl_surf)
dCZ_ddelta_s = (CZ_delta_s_prime - CZ_0) / (delta_ctrl_surf)
dCL_ddelta_s = (CL_delta_s_prime - CL_0) / (delta_ctrl_surf)
dCM_ddelta_s = (CM_delta_s_prime - CM_0) / (delta_ctrl_surf)
dCN_ddelta_s = (CN_delta_s_prime - CN_0) / (delta_ctrl_surf)
conditions.static_stability.derivatives.Clift_delta_s = dClift_ddelta_s
conditions.static_stability.derivatives.Cdrag_delta_s = dCdrag_ddelta_s
conditions.static_stability.derivatives.CX_delta_s = dCX_ddelta_s
conditions.static_stability.derivatives.CY_delta_s = dCY_ddelta_s
conditions.static_stability.derivatives.CZ_delta_s = dCZ_ddelta_s
conditions.static_stability.derivatives.CL_delta_s = dCL_ddelta_s
conditions.static_stability.derivatives.CM_delta_s = dCM_ddelta_s
conditions.static_stability.derivatives.CN_delta_s = dCN_ddelta_s
# Stability Results
conditions.S_ref = S_ref
conditions.c_ref = c_ref
conditions.b_ref = b_ref
conditions.X_ref = X_ref
conditions.Y_ref = Y_ref
conditions.Z_ref = Z_ref
return
[docs]
def compute_stability_derivative(sub_sur,trans_sur,sup_sur,h_sub,h_sup,Mach):
if trans_sur == None and sup_sur == None:
derivative = h_sub(Mach)*sub_sur(Mach)
return derivative
derivative = h_sub(Mach)*sub_sur(Mach) + (1 - (h_sup(Mach) + h_sub(Mach)))*trans_sur(Mach) + h_sup(Mach)*sup_sur(Mach)
return derivative
[docs]
def compute_coefficients(sub_sur_Clift,sub_sur_Cdrag,sub_sur_CX,sub_sur_CY,sub_sur_CZ,sub_sur_CL,sub_sur_CM,sub_sur_CN,
trans_sur_Clift,trans_sur_Cdrag,trans_sur_CX,trans_sur_CY,trans_sur_CZ,trans_sur_CL,trans_sur_CM,trans_sur_CN,
sup_sur_Clift,sup_sur_Cdrag,sup_sur_CX,sup_sur_CY,sup_sur_CZ,sup_sur_CL,sup_sur_CM,sup_sur_CN,
h_sub,h_sup,Mach, pts):
# subsonic
sub_Clift = np.atleast_2d(sub_sur_Clift(pts)).T
sub_Cdrag = np.atleast_2d(sub_sur_Cdrag(pts)).T
sub_CX = np.atleast_2d(sub_sur_CX(pts)).T
sub_CY = np.atleast_2d(sub_sur_CY(pts)).T
sub_CZ = np.atleast_2d(sub_sur_CZ(pts)).T
sub_CL = np.atleast_2d(sub_sur_CL(pts)).T
sub_CM = np.atleast_2d(sub_sur_CM(pts)).T
sub_CN = np.atleast_2d(sub_sur_CN(pts)).T
if trans_sur_Clift == None and sup_sur_Clift == None:
results = Data()
results.Clift = h_sub(Mach)
results.Cdrag = h_sub(Mach)
results.CX = h_sub(Mach)
results.CY = h_sub(Mach)
results.CZ = h_sub(Mach)
results.CL = h_sub(Mach)
results.CM = h_sub(Mach)
results.CN = h_sub(Mach)
return results
# transonic
trans_Clift = np.atleast_2d(trans_sur_Clift(pts)).T
trans_Cdrag = np.atleast_2d(trans_sur_Cdrag(pts)).T
trans_CX = np.atleast_2d(trans_sur_CX(pts)).T
trans_CY = np.atleast_2d(trans_sur_CY(pts)).T
trans_CZ = np.atleast_2d(trans_sur_CZ(pts)).T
trans_CL = np.atleast_2d(trans_sur_CL(pts)).T
trans_CM = np.atleast_2d(trans_sur_CM(pts)).T
trans_CN = np.atleast_2d(trans_sur_CN(pts)).T
# supersonic
sup_Clift = np.atleast_2d(sup_sur_Clift(pts)).T
sup_Cdrag = np.atleast_2d(sup_sur_Cdrag(pts)).T
sup_CX = np.atleast_2d(sup_sur_CX(pts)).T
sup_CY = np.atleast_2d(sup_sur_CY(pts)).T
sup_CZ = np.atleast_2d(sup_sur_CZ(pts)).T
sup_CL = np.atleast_2d(sup_sur_CL(pts)).T
sup_CM = np.atleast_2d(sup_sur_CM(pts)).T
sup_CN = np.atleast_2d(sup_sur_CN(pts)).T
# apply
results = Data()
results.Clift = h_sub(Mach)*sub_Clift + (1 - (h_sup(Mach) + h_sub(Mach)))*trans_Clift + h_sup(Mach)*sup_Clift
results.Cdrag = h_sub(Mach)*sub_Cdrag + (1 - (h_sup(Mach) + h_sub(Mach)))*trans_Cdrag + h_sup(Mach)*sup_Cdrag
results.CX = h_sub(Mach)*sub_CX + (1 - (h_sup(Mach) + h_sub(Mach)))*trans_CX + h_sup(Mach)*sup_CX
results.CY = h_sub(Mach)*sub_CY + (1 - (h_sup(Mach) + h_sub(Mach)))*trans_CY + h_sup(Mach)*sup_CY
results.CZ = h_sub(Mach)*sub_CZ + (1 - (h_sup(Mach) + h_sub(Mach)))*trans_CZ + h_sup(Mach)*sup_CZ
results.CL = h_sub(Mach)*sub_CL + (1 - (h_sup(Mach) + h_sub(Mach)))*trans_CL + h_sup(Mach)*sup_CL
results.CM = h_sub(Mach)*sub_CM + (1 - (h_sup(Mach) + h_sub(Mach)))*trans_CM + h_sup(Mach)*sup_CM
results.CN = h_sub(Mach)*sub_CN + (1 - (h_sup(Mach) + h_sub(Mach)))*trans_CN + h_sup(Mach)*sup_CN
return results
[docs]
def compute_coefficient(sub_sur_coef,trans_sur_coef, sup_sur_coef, h_sub,h_sup,Mach, pts):
# subsonic
sub_coef = np.atleast_2d(sub_sur_coef(pts)).T
if trans_sur_coef == None and sup_sur_coef == None:
coef = h_sub(Mach)
return coef
# transonic
trans_coef = np.atleast_2d(trans_sur_coef(pts)).T
# supersonic
sup_coef = np.atleast_2d(sub_sur_coef(pts)).T
# apply
coef = h_sub(Mach)*sub_coef + (1 - (h_sup(Mach) + h_sub(Mach)))*trans_coef + h_sub(Mach)*sup_coef
return coef
