A supersonic wind tunnel of circular cross-section is to be designed to produce a Mach 4.5 airflow in its test section. The flow is to be supplied from a nozzle upstream, with a stagnation pressure of 70 kPa and a stagnation temperature of 288 K. Both the nozzle inlet and test section are 0.15 m in diameter. Po = 70 kPa To = 288 K Dia. = 0.15 m Inlet Throat Assuming isentropic flow, determine the following: the area of the throat. (b) the temperature and pressure in the test section. (c) the Mach number at the nozzle inlet. (d) the mass flow rate through the wind tunnel. Exit Me = 4.5 Test section Dia. = 0.15 m Test section