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Discussion :: GATE Aeronautical Engineering

  1. A rocket motor has combustion chamber temperature of 2600 K and the products have molecular weight of 25 g/mol and ratio of specific heats 1.2. The universal gas constant is 8314 J/kg-mole-K. The value of theoretical c* (in m/s) is ____.
    2. A.
    1430 to 1440
    B.
    1540 to 1550
    C.
    1380 to 1390
    D.
    1311 to 1312

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    Workspace

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    Answer : Option A

    Explanation :

    -NA-

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