Question: Air flows from a supersonic nozzle with a throat diameter of 6.5 cm into a 13-cmdiameter pipe. The stagnation pressure at the inlet to the pipe is 700 kPa. At distances of 5 and 33 diameters from the inlet to the pipe, the static pressures are measured and found to be 24.5 and 50 kPa, respectively. Determine the Mach numbers at these two sections and the mean friction factor between the two sections. The flow in the nozzle can be assumed to be isentropic and the flow in the pipe can be assumed to be adiabatic.