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.

a) specific impulse = 203 s

(b) mass flow rate = 2511 kg/s

(c) throat diameter = 0.774 m

(d) exit diameter = 1.95 m

(e) thrust =  5.3*10^6 N/m^2

(f) thrust at sea level = 15.6*10^6 N

(g) thrust with hydrogen = 5*10^6 N

(h) thrust with stagnation =  5*10^6 N

Explanation:

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explanation:

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