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Discussion :: GATE Aeronautical Engineering

  1. A rocket motor has a chamber pressure of 100 bar and chamber temperature of 3000 K. The ambient pressure is 1 bar. Assume that the specific heat at constant pressure is 1 kJ/kg-K. Also assume that the flow in the nozzle is isentropic and optimally expanded. The exit static temperature in K is
    2. A.
    805
    B.
    845
    C.
    905
    D.
    945

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    Workspace

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    Answer : Option A

    Explanation :

    -NA-

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