A rocket motor is being designed to operate at sea level, where the pressure is 100 kPa
Chapter 12, Problem 12.55(choose chapter or problem)
A rocket motor is being designed to operate at sea level, where the pressure is 100 kPa absolute. The chamber pressure (total pressure) is 2.0 MPa, and the chamber temperature (total temperature} is 3300 K. The throat area of the nozzle is 10 cm2 The ratio of the specific heats (k) of the exhaust gas is 1.2, and the gas constant is 400 J/kg K. a. Determine the nozzle expansion ratio that is required to achieve an ideally expanded nozzle, and determine the nozzle thrust under these conditions (see Prob. 12.53 for the thrust equation). b. Determine the thrust that would be obtained if the expansion ratio were reduced by 10% to achieve an underexpanded nozzle.
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