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 surfaces are given by p_u = 4x 10⁴(x- l)² + 5.4 x 10⁴, p₁ = 2x 10⁴(x- 1)² + 1.73 x 10⁵, τ_u = 288x ^–0.2, and τ₁ = 731x^–0.2, respectively, where x is the distance from the leading edge in meters and p and τ are in Newton’s 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.