Thin airfoil theory ($c_l\simeq 2\pi (\alpha -{\alpha }_{L=0})$)

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.