The gas entering a rocket nozzle has a stagnation pressure of 1500 kpa and a stagnation temperature of 3000 °c. the rocket is traveling in the still standard atmosphere at 30,000 m. find the throat and exit area for a flow rate of 10 kg/s. assume k = 1.35, r = 287.0 n ∙ m/kg ∙ k. the gas is perfectly, expanded to the ambient pressure.