distribution p given by Consider a circular airfoil with a surface pressure p = P + = pU - 2U (sin 0 sin 3), (3.19) where U and P are flow velocity and pressure far away; p is fluid mass density supposed uniform; 0 is angular position measured from the horizontal anti-clockwise, and gives the angular position of the stagnation points. (1) Find the lift and the drag. (2) Find the moment about a normal centroidal axis.