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Discussion :: GATE Aeronautical Engineering

  1. An aircraft is flying at Mach number M = 1.5, where the ambient temperature is 250 K. The stagnation temperature of gases at the entry to the nozzle is 800 K. The nozzle is choked and always under expanded. Assume the molecular weight of the exhaust gases to be 29, the ratio of specific heats to be 1.4 and the universal gas constant is 8314 J/kmol-K. 
    For which one of the nozzle exit Mach numbers given below is the propulsive efficiency highest?
    2. A.
    1
    B.
    1.5
    C.
    2
    D.
    2.5

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    Answer : Option A

    Explanation :

    -NA-

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