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Discussion :: GATE Aeronautical Engineering

  1. A solid propellant of density 1800 kg/m3 has a burning rate law r = 6.65 x 10-3p0.45 mm/s, where p is pressure in Pascals. It is used in a rocket motor with a tubular grain with an initial burning area of 0.314 m2. The characteristic velocity is 1450 m/s. What should be the nozzle throat diameter to achieve an equilibrium chamber pressure of 50 bar at the end of the ignition transient?
    2. A.
    35 mm
    B.
    38 mm
    C.
    41 mm
    D.
    45 mm

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    Answer : Option B

    Explanation :

    -NA-

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