Air is supplied to a convergent–divergent nozzle from a large tank in which the pressure and temperature are kept at 700 kPa and 40°C, respectively. If the nozzle has an exit area that is 1.6 times the throat area and if a normal shock occurs in the nozzle at a section where the area is 1.2 times the throat area, find the pressure, temperature, and Mach number at the nozzle exit. Assume one-dimensional, isentropic flow.