Engineering, 18.07.2019 05:40 brianna8739
Gas entering a rocket nozzle has a stagnation pressure of 1500 kpa and a stagnation temperature of 3000°c. the gas (k =1.35, r= 287.0 nm/kgk) expands isentropically to the ambient pressure. the rocket travels in standard atmosphere at 30,000 m. determine: a)- mach number at nozzle exit b)- throat and exit area [m^2] for a flow rate of 10 kg/s
Answers: 3
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Gas entering a rocket nozzle has a stagnation pressure of 1500 kpa and a stagnation temperature of 3...
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