Compressible lift slope for the finite wing Calculator

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)

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