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Thin Airfoil Lift Equation

The fundamental linear relationship for lift:

L' = \rho U_{\infty} \Gamma

. For 2D flow,

L' = \frac{1}{2} \rho U_{\infty}^2 c \cdot 2\pi \alpha

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The statement of the theorem

The lift force per unit span

L'

is governed by the Kutta-Joukowski theorem:

L' = \rho U_{\infty} \Gamma

For a 2D flow over a chord

c

, the lift force

L'

is approximated by:

L' \approx \frac{1}{2} \rho U_{\infty}^2 c \cdot 2\pi \alpha

where

\rho

is the fluid density and

U_{\infty}

is the freestream velocity.

Source: Wikipedia