Consider an infinitely thin flat plate with a 1 m chord at an angle of attack of 10° in a supersonic flow. The pressure and shear stress distributions on the upper and lower surfaces are given by , , , and , respectively, where x is the distance from the leading edge in meters and p and τ are in N/m2 . Calculate the normal and axial forces, lift and drag, moment about the leading edge and moment about the quarter chord point, all per unit span. Also, calculate the locations of the center of pressure.