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Angle of Attack ($\\alpha$)

The angle between the relative airflow and the chord line of the airfoil. It is the primary variable determining the lift generated.
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The statement of the theorem

Define the angle of attack α\alpha as the angle between the freestream velocity vector U⃗∞\vec{U}_{\infty} and the chord line c⃗\vec{c} of the airfoil. Mathematically, if U⃗∞\vec{U}_{\infty} has direction θ∞\theta_{\infty} and the chord line is aligned with the x-axis (θc=0\theta_c = 0), then α=θ∞\alpha = \theta_{\infty}. The relative velocity v⃗rel\vec{v}_{rel} is given by v⃗rel=U⃗∞−v⃗induced\vec{v}_{rel} = \vec{U}_{\infty} - \vec{v}_{induced}.