RCAIDE.Library.Methods.Aerodynamics.Vortex_Lattice_Method.evaluate_VLM.evaluate_no_surrogate#
- evaluate_no_surrogate(state, settings, base_vehicle)[source]#
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
- Parameters:
aerodynamics – VLM analysis [unitless]
state – flight conditions [unitless]
settings – VLM analysis settings [unitless]
vehicle – vehicle configuration [unitless]
- Returns:
None