Menu
Home / GATE 2017-2018 / GATE Aeronautical Engineering :: Discussion

Discussion :: GATE Aeronautical Engineering

  1. The stagnation temperatures at the inlet and exit of a combustion chamber are 600 K and 1200 K, respectively. If the heating value of the fuel is 44 MJ/kg and specific heat at constant pressure for air and hot gases are 1.005 kJ/kg.K and 1.147 kJ/kg.K respectively, the fuel-to-air ratio is
    2. A.
    0.0018
    B.
    0.018
    C.
    0.18
    D.
    1.18

    View Answer

    Workspace

    View Answer

    Answer : Option B

    Explanation :

    -NA-

Write your comments here:

Be The First To Comment