Air at 500 K flows through a converging-diverging nozzle with throat area of 1 cm2 and exit area of 2.7 cm2. When the mass flow is 182.2 kg/h, a Pitot-static probe placed in the exit plane reads p0 = 250.6 kPa and p = 240.1 kPa. Estimate the exit velocity. Is there a normal shock wave in the duct? If so, compute the Mach number just downstream of this shock.