Air flows over a 20 included angle wedge at Mach = 8 at an altitude where atmospheric pressure, Patm = 20,000 Pascal absolute. The wedge is 0.492 m long. Calculate the drag on the wedge. Hints: 20 0.492 m Calculate the pressure on the top and the bottom surface Calculate the Mach number after the oblique shock Calculate the total pressure after the oblique shock Calculate the pressure on the back surface Calculate the drag