A rocket motor operates at an altitude where the atmospheric pressure is 30 kPa. The
Chapter 12, Problem 12.54(choose chapter or problem)
A rocket motor operates at an altitude where the atmospheric pressure is 30 kPa. The expansion ratio of the nozzle is 4 (exit area/throat area). The chamber pressure of the motor (total pressure) is 1.2 MPa, and the chamber temperature (total temperature) is 3000C. The ratio of the specific heats of the exhaust gas is 1.2, and the gas constant is 400 }/kg K. The throat area of the rocket nozzle is 100 cm2 a . Determine the Mach number, density, pressure, and velocity at the nozzle exit. b. Determine the mass flow rate. c. Calculate the thrust of the rocket using T = mV, + (p, - Po)A, d. What would the chamber pressure of the rocket have to be to have an ideally expanded nozzle? Calculate the rocket thrust under this condition.
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