The lift curve slope for a finite wing, often denoted as “a,” is an aerodynamic parameter that quantifies the rate of change of lift coefficient (“CL”) with respect to changes in the angle of attack (“α”) for an aircraft wing with finite span. In other words, it represents how much additional lift is generated for a given change in angle of attack.
- a is the lift curve slope for the finite wing.
- a0 is the lift curve slope for an equivalent elliptical wing (a reference value).
- AR is the aspect ratio of the wing.
- 𝜏 is the downwash effect factor, which accounts for the influence of trailing vortices on the local angle of attack experienced by the wing.