Consider a rectangular wing mounted in a low-speed wind tunnel. The wing model completely spans the test section so that the flow is essentially two-dimensional. If the wing has an NACA 4415 airfoil section and a chord of 0.3 meters, calculate the lift, drag, and pitching moment about the quarter-chord per unit span when the pressure, temperature, and velocity are 1 atm., 303K, and 42 m/sec., respectively. The angle of attack is 8°. What is the moment about the leading edge for these conditions?