Air enters a convergent divergent nozzle of a rocket engine at a stagnation temperature of 3200 K. The nozzle exhausts into an ambient pressure of 100 kPa and the exit-to-throat area ratio is 10. The thrust produced is 1300 kN. Assume the expansion process to be complete and isentropic. Determine (a) the exit velocity and static temperature, (b) mass flow rate, (c) stagnation pressure, (d) throat and exit areas.