Thin airfoil theory
= Thin airfoil theory
{title2=$c_l\simeq2\pi(\alpha-\alpha_{L=0})$}
A small-disturbance, two-dimensional <potential flow> model for a thin <airfoil>, using surface tangency and smooth flow departure at its trailing edge to determine <circulation>. Its <lift coefficient> slope is $2\pi$ per <radian>, with camber shifting the zero-lift <angle of attack>. See <airfoil> for assumptions, examples and the <aerodynamic stall> limit.