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Kutta-Joukowski Theorem

States that the lift force per unit span (L') generated by an airfoil is directly proportional to the fluid density (\rho), the velocity (V), and the circulation (\Gamma) around the airfoil: L' = \rho V \Gamma.

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The statement of the theorem

Let

\rho

be the fluid density,

\mathbf{V}_{\infty}

be the uniform free-stream velocity (magnitude

V

), and

C

be the airfoil contour. Define the circulation

\Gamma

around

C

as the line integral of the tangential component of the velocity

\mathbf{V}

relative to the free stream: \n

\Gamma = \oint_C \mathbf{V} \cdot d\mathbf{l}

\nThen, the lift force per unit span,

L'

, acting on the airfoil

C

is given by the Kutta-Joukowski Theorem:\n

L' = \rho V \Gamma

Source: Wikipedia