RCAIDE.Library.Methods.Aerodynamics.Vortex_Lattice_Method.evaluate_VLM

evaluate_VLM#

Functions

compute_coefficients(sub_sur_Clift, ...)

compute_stability_derivative(sub_sur, ...)

create_conditions(n_cpts, altitude, g, V, ...)

evaluate_no_surrogate(state, settings, vehicle)

Evaluates forces and moments directly using VLM.

evaluate_surrogate(state, settings, vehicle)

Evaluates forces and moments using built surrogates
evaluate_surrogate(state, settings, vehicle)[source]#

Evaluates forces and moments using built surrogates

Assumptions:

  • Drag due to angle of attack is the dominant drag component and the only one calculated

  • Aircraft is symmetric such that CY_L_0 = 0 and CN_L_0 = 0

Source:

None

Parameters:

  • aerodynamics – VLM analysis [unitless]

  • state – flight conditions [unitless]

  • settings – VLM analysis settings [unitless]

  • vehicle – vehicle configuration [unitless]

Returns:

None

evaluate_no_surrogate(state, settings, vehicle)[source]#

Evaluates forces and moments directly using VLM.

Assumptions:

Source:

None

Parameters:

  • aerodynamics – VLM analysis [unitless]

  • state – flight conditions [unitless]

  • settings – VLM analysis settings [unitless]

  • vehicle – vehicle configuration [unitless]

Returns:

None

create_conditions(n_cpts, altitude, g, V, MAC, energy_conditions)[source]#
compute_stability_derivative(sub_sur, trans_sur, sup_sur, h_sub, h_sup, Mach)[source]#
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, sub_sur_cl_spanwise, trans_sur_cl_spanwise, sup_sur_cl_spanwise, h_sub, h_sup, Mach, pts)[source]#