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5. (2.5 pts) Consider the geometry shown below. Here a supersonic flow with Mach number, pressure, and temperature M, P, and T., respectively, is deflected through an angle 8, by a compression comer at point A on the lower wall, creating an oblique shock wave emanating from point A. This shock impinges on the upper wall at point B. Also precisely at point B the upper wall is bent downward through the angle 02. The incident shock is reflected at point B, creating a reflected shock which propagates downward and to the right in the figure below. Consider a flow where M1 = 3, P1 = 1 atm, and T, = 300 K. Consider the geometry as sketched in the figure below where 0, = 14 and 0; = 10: Calculate the Mach number, pressure, and temperature in region 3 behind the reflected shock wave. o fecadent stock M, PA 73 Reflected shock