Question: A uniform air flow over a plane wall at Mach 2.2 and with a temperature of 270 K and a pressure of 90 kPa is deflected downward by the changes in the wall direction shown in Figure. Determine the Mach numbers, the pressures, and the stagnation pressures in regions 2 and 3 shown in Figure. Sketch the oblique shock waves generated by the changes in wall direction and on this sketch indicate the angles that the shock waves make to the initial flow direction. Determine the maximum turning angle that the second wall segment can have (15° in the above calculation) if the second shock wave is to remain attached to this wall segment.
