1. A wedge with semi-angle = 20° is moving through air (T = 200 K, Pr = 0.7225 and y = 1.4) at a Mach number more than one. The wedge is kept at temperature Twall = 1600 K. Calculate the free-stream Mach number, Ma.., at which the wedge wall temperature becomes equal to the adiabatic wall temperature of the boundary layer. What is the corresponding Mach number at the edge of the boundary layer, Maę? Hint: Assume that the recovery factor is equal to √Pr, the gas is calorically perfect, and ignore the effect of boundary layer on the inviscid flow. (30 points) Ma∞ > 1 Tw B 20 shock 20B boundary-layer edgé u(y) Mae, Pes Tes He

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