= 1.4. Assuming The ambient pressure is pa = 0.1 MPa, and the specific heat ratio...

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= 1.4. Assuming The ambient pressure is pa = 0.1 MPa, and the specific heat ratio of a propellant is a propellant of molecular weight M = 17 kg/kmol and flame temperature of Tad = 3400 K, (a) determine the rocket throat and exhaust areas required for a thrust of 525 kN and an ideal specific impulse of Isp = 275 sec. (b) determine the thrust that this rocket would develop if the ambient pressure were changed to Pa = 0.03 MPa. (c) How much thrust would be developed by a rocket designed to expand to pe = 0.03 MPa if it had the same stagnation (combustion chamber) conditions, throat area, and propellant? = 1.4. Assuming The ambient pressure is pa = 0.1 MPa, and the specific heat ratio of a propellant is a propellant of molecular weight M = 17 kg/kmol and flame temperature of Tad = 3400 K, (a) determine the rocket throat and exhaust areas required for a thrust of 525 kN and an ideal specific impulse of Isp = 275 sec. (b) determine the thrust that this rocket would develop if the ambient pressure were changed to Pa = 0.03 MPa. (c) How much thrust would be developed by a rocket designed to expand to pe = 0.03 MPa if it had the same stagnation (combustion chamber) conditions, throat area, and propellant?