RCAIDE.Library.Methods.Aerodynamics.Common.Drag.total_drag
total_drag#
- total_drag(state, settings, geometry)[source]#
Computes the total drag of an aircraft.
- Assumptions:
None
- Source:
None
- Parameters:
settings. – drag_coefficient_increment (float): drag_coefficient_increment [Unitless]
state.conditions.aerodynamics.coefficients.drag. – trim_corrected_drag (numpy.ndarray): trim corrected drag [Unitless] spoiler_drag (numpy.ndarray): spoiler drag [Unitless]
geometry (dict) – aircraft data structure [-]
- Returns:
None