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SOLVED:Consider supersonic flow past the thin airfoil shown in Fig. P10.1. The airfoil is symmetric about the chord line. Use linearized theory to develop expressions for the lift coefficient, the drag coefficient, and the pitching-moment coefficient about the midchord. The resultant expressions should include the free-stream Mach number, the constants a1 and a2, and the thickness ratio t / c(=τ). Show that, for a fixed thickness ratio, the wave drag due to thickness is a minimum when a1=a2=0.4.
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