acomp (Compressible Lift Slope for Finite Wing): This parameter 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. This formula provides a means to estimate the lift slope () for a high aspect ratio wing operating in compressible flow conditions based on its incompressible lift curve slope (), freestream Mach number (), Oswald efficiency factor (), and aspect ratio ().
- Lift slope for a high aspect ratio straight wing in a compressible flow (acomp) in per rad
- Lift slope for an infinite wing in an incompressible flow (a0) in per rad
- Freestream Mach number (M∞)
- Span Efficiency Factor (e1)
- Aspect Ratio (AR)