The gas entering a rocket nozzle (i.e. converging-diverging nozzle) has a stagnation pressure of 1500kPa and a stagnation temperature of 3273K. The rocket is travelling in the atmosphere at 30,000m, where the ambient pressure is 1.197kPa. Assume gamma =1.35,R=287.0(J)/(k)(g)/(K).
a. Find the throat and exit area for a flow rate of 10k(g)/(s) and perfect expansion.
b. With the geometry you found in part a, at what atmospheric pressure will a shock begin to form in the nozzle?
4. The gas entering a rocket nozzle (i.e. converging-diverging nozzle) has a stagnation pressure of 1500 kPa and a stagnation temperature of 3273 K.The rocket is travelling in the atmosphere at
30,000 m, where the ambient pressure is 1.197 kPa. Assume Y = 1.35, R = 287.0 J/kg/K a. Find the throat and exit area for a flow rate of 10 kg/s and perfect expansion.
b. With the geometry you found in part a, at what atmospheric pressure will a shock begin to form in the nozzle?