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) specific impulse,
(b) mass flow rate,
(c) throat diameter,
(d) exit diameter. For the same nozzle find (e) thrust at 30-kM altitude; (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.