Question: A uniform air flow over a plane wall at Mach 2.2 and with a temperature of 325 K encounters a symmetrical triangular "bump" on the wall. The upstream and downstream faces of this bump are at an angle of 15° to the plane wall over which the air is flowing. The situation being considered is as shown in Figure. Find the Mach numbers and temperatures in the flows over the upstream and downstream faces of the "bump" and in the flow over the wall downstream of the bump, i.e., find the Mach numbers and temperatures in the flow regions 2, 3, and 4 shown in Figure.
