Question: 4. A rocket combustion chamber is designed for a stagnation pressure of 50 MPa. f this rocket is to operate between sea level, where

4. A rocket combustion chamber is designed for a stagnation pressure of 50 MPa. f this rocket is to operate between sea level, where the pressure is 101 kPa, and at an altitude of 85 km, where the pressure is 5 kPa, what would be the range of nozzle area ratios required for correct expansion at all altitudes? Assume isentropic flow in the nozzle with a specific heat ratio of 1.25. If the rocket is to be operated in space, what would be the required nozzle area ratio for correct expansion? [15 Marks]

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