Compressible Lift Slope for Finite Wing represents the rate of change of lift coefficient (Cl) with respect to the angle of attack (α) for a finite wing in compressible flow conditions. It takes into account the effects of compressibility on the wing’s lift behavior. The equation essentially combines the effects of a0,comp, e₁, and AR to determine how the lift slope of a finite wing in compressible flow (acomp) behaves. It takes into account the deviation from idealized behavior and the aerodynamic characteristics of the wing’s shape and span.
- Compressible lift slope for the finite wing (acomp) in per rad
- Lift slope for an infinite wing in a subsonic compressible flow (a0,comp) in per rad
- Span efficiency factor (e₁)
- Aspect ratio (AR)