RCAIDE.Library.Methods.Aerodynamics.Common.Lift.compute_flap_lift
compute_flap_lift#
- compute_flap_lift(t_c, flap_type, flap_chord, flap_angle, sweep, wing_Sref, wing_affected_area)[source]#
Computes the increase of lift due to trailing edge flap deployment
Assumptions: None
Source: Unknown
Inputs: t_c (wing thickness ratio) [Unitless] flap_type [string] flap_c_chord (flap chord as fraction of wing chord) [Unitless] flap_angle (flap deflection) [radians] sweep (Wing sweep angle) [radians] wing_Sref (Wing reference area) [m^2] wing_affected_area (Wing area affected by flaps) [m^2]
Outputs: dcl_max_flaps (Lift coefficient increase) [Unitless]
Properties Used: N/A