A rocket is to be designed to produce 5 MN of thrust at sea level. The pressure in the combustion chamber is 7 MPa and the temperature is 2800 K.
If the working fluid is assumed to be a perfect gas with the properties of air at room temperature, determine the following:
(a) the specific impulse (s), (b) the propellant mass flowrate (kg/s), (c) the throat diameter (m), and (d) the nozzle exit diameter (m).
For the same nozzle find:
(e) the thrust at an altitude of 30 km (MN), (f) thrust at sea level if chamber pressure were increased to 21 MPa, (g) thrust with hydrogen at the same inlet stagnation conditions, and (h) thrust with stagnation temperature increased to 3600 K.2.