RCAIDE.Library.Methods.Aerodynamics.Vortex_Lattice_Method.evaluate_VLM.evaluate_surrogate#

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