RCAIDE.Library.Methods.Aerodynamics.Common.Lift.fuselage_correction
fuselage_correction#
- fuselage_correction(state, settings, geometry)[source]#
Corrects aircraft lift based on fuselage effects
- Assumptions:
None
- Source:
adg.stanford.edu (Stanford AA241 A/B Course Notes)
- Parameters:
settings.fuselage_lift_correction (float) – fuselage lift correction [unitless]
state.conditions. – freestream.mach_number (numpy.ndarray): mach number [unitless] aerodynamics.angles.alpha (numpy.ndarray): angle of attack [radians] aerodynamics.coefficients.lift (numpy.ndarray): lift coefficient [unitless]
- Returns:
lift coefficient [unitless]
- Return type:
aircraft_total_lift (numpy.ndarray)