The lift slope (a) for a finite wing is a parameter used to describe the change in lift coefficient (CL) with respect to the geometric angle of attack (α) of the wing. It is a measure of the wing’s effectiveness in generating lift as the angle of attack is varied. The lift slope represents the linear relationship between the lift coefficient and the geometric angle of attack for a given wing configuration. It quantifies the rate at which lift increases or decreases as the angle of attack changes.
- a is the lift slope (also known as the lift-curve slope or lift-curve gradient) for the finite wing.
- a0 is the lift slope for an infinite wing (an airfoil with an infinite span)
- AR is the aspect ratio of the finite wing, defined as the square of the wingspan (b) divided by the wing area (A).
- τ is the correction factor that accounts for the wing’s planform shape and twist.