Aconvergent-divergent nozzle is designed to operate with an exit mach number of 2.0. the nozzle is supplied from an air reservoir in which the pressure is 500 kpa; the temperature is 500 k. the nozzle throat area is 5 cm2. assume air to behave as a perfect gas, with \gamma= 1.4 and r = 0.2870 kj/kgk.

(a) determine the ratio of exit area to throat area.

(b) given the area ratio in part (a), find the range of back pressure over which the nozzle is choked.

(c) determine the mass-flow rate for a back pressure of 450 kpa.

(d) determine the mass-flow rate for a back pressure of 0 kpa.