The performance of a rocket with a 200-mm diameter nozzle exit is tested on a st
ID: 1921036 • Letter: T
Question
The performance of a rocket with a 200-mm diameter nozzle exit is tested on a stand as shown in Figure 4.79. Under the conditions of a particular test, atmospheric pressure is 101 kPa, the exhaust gas has an exit velocity of 1500 m/s, a pressure of 150 kPa absolute, and a mass flow rate of 10 kg/s. (a) Estimate the thrust generated by the rocket. (b) How is the mass flow rate of the exhaust gas related to the fuel consumption rate of the rocket?
The performance of a rocket with a 200-mm diameter nozzle exit is tested on a stand as shown in Figure 4.79. Under the conditions of a particular test, atmospheric pressure is 101 kPa, the exhaust gas has an exit velocity of 1500 m/s, a pressure of 150 kPa absolute, and a mass flow rate of 10 kg/s. (a) Estimate the thrust generated by the rocket. (b) How is the mass flow rate of the exhaust gas related to the fuel consumption rate of the rocket?Explanation / Answer
Fuel consumption rate is the same as mass flow rate of the exhaust gases i.e. 10 kg/s
For the first part we have,
Pressure force = 49 * pi * 0.1^2 = 1539.38 N
Force due to the exhaust gases = mass flow rate * velocity of exhaust = 1500*10 = 15000 N
Hence the total thrust generated by the rocket is 15000 + 1539.38 = 16539.38 N
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