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 pu = 4 × 104 (x − 1)2 + 5.4 × 104 , pl = 2 × 104 (x − 1)2 + 1.73 × 105 , τu = 288x −0.2 , and τl = 731x −0.2 , where x is the distance from the leading edge in meters and p and τ are in Newtons per square meter. Calculate the normal and axial forces, the lift and drag, moments about the leading edge, and moments about the quarter chord, all per unit span. Also calculate the location of the center of pressure.