Air supplied from a reservoir at 750 kPa & 450 K is to flow through a converging- diverging nozzle with a throat area of 20 cm. sq. To reach a supersonic design pressure of 101 kPa at the exit plane of the nozzle: a) What must be the nozzle exit area? b) What is the corresponding supersonic design Mach number? c) What will be exit plane temperature and velocity? d) Calculate the mass flow rate through the nozzle.