Supersonic airflow enters an adiabatic, constant area (inside diameter = 1 ft) 30-ft-long pipe with Ma1 = 3.0. The pipe friction factor is estimated to be 0.02. What ratio of pipe exit pressure to pipe inlet stagnation pressure would result in a normal shock wave standing at
(a) x = 5 ft, or
(b) x = 10 ft, where x is the distance downstream from the pipe entrance? Determine also the duct exit Mach number and sketch the temperature-entropy diagram for each situation.