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Discussion :: GATE Aeronautical Engineering

  1. A bipropellant liquid rocket motor operates at a chamber pressure of 40 bar with a nozzle throat diameter of 50 mm. The characteristic velocity is 1540 m/s. If the fuel-oxidizer ratio of the propellant is 1.8, and the fuel density is 900 kg/m3, what should be the minimum fuel tank volume for a burn time of 8 minutes
    2. A.
    1.65 m3
    B.
    1.75 m3
    C.
    1.85 m3
    D.
    1.95 m3

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    Answer : Option B

    Explanation :

    -NA-

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