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Discussion :: GATE Aeronautical Engineering

  1. Data for an airplane are given as follows: weight W = 30kN, thrust available at sea-level T0 = 4000 N, wing planform area S = 30 m2, maximum lift coefficient CL max = 1.4, and drag coefficient CD = 0.015 + 0.024 C2L. Assume air density at sea-level P∞ = 1.22 kg/ m3.
    Stall speed of the airplane in m/s is
    2. A.
    17.36
    B.
    34.22
    C.
    45.52
    D.
    119.46

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    Answer : Option B

    Explanation :

    -NA-

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