The shock waves on a vehicle in supersonic flight cause a component of drag called supersonic wave drag, Dw. Define the wave-drag coefficient as CDw = Dw/q∞ S, where S is a suitable reference area for the body. In supersonic flight, the flow is governed in part by its thermodynamic properties, given by the specific heats at constant pressure, cp, and at constant volume, cv. Define the ratio cp/cv= γ. Using Buckingham's pi theorem, show that CD,w =/(M∞, γ). Neglect the influence of friction.