RCAIDE.Library.Methods.Aerodynamics.Common.Drag.induced_drag
induced_drag#
- induced_drag(state, settings, geometry)[source]#
Determines induced drag for the full aircraft
Assumptions: This function operates in one of three ways:
-An oswald efficiency is provided. All induced drag, inviscid and viscous, is use calculated using that factor -A span efficiency is provided. The inviscid induced drag is calculated from that. Viscous induced drag is
calculated using the viscous_lift_dependent_drag_factor, K, and the parasite drag.
- -The inviscid induced drag from the the lift calculation for each wing, usually a vortex lattice, is used. Viscous induced drag is
calculated using the viscous_lift_dependent_drag_factor, K, and the parasite drag.
The last two options do not explicitly provide for the case where the fuselage produces an induced drag directly.
Source: adg.stanford.edu (Stanford AA241 A/B Course Notes) http://aerodesign.stanford.edu/aircraftdesign/aircraftdesign.html
Inputs: state.conditions.aerodynamics.
lift_coefficient [Unitless] lift_breakdown.inviscid_wings[wings.*.tag] [Unitless] drag_breakdown.induced.inviscid [Unitless] drag_breakdown.induced.inviscid_wings[wings.*.tag] [Unitless] drag_breakdown.parasite[wings.*.tag].parasite_drag_coefficient [Unitless] drag_breakdown.parasite[wings.*.tag].reference_area [m^2]
settings.oswald_efficiency_factor [Unitless] settings.viscous_lift_dependent_drag_factor [Unitless] settings.span_efficiency [Unitless]
Outputs: conditions.aerodynamics.coefficients.drag.induced.
total [Unitless] viscous [Unitless] oswald_efficiency_factor [Unitless] viscous_wings_drag [Unitless]
total_induced_drag [Unitless]
Properties Used: N/A