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Discussion :: GATE Aeronautical Engineering

  1. Consider a thin flat plate airfoil at a small angle x to an oncoming supersonic stream of air. Assuming the flow to be inviscid, Cd / C2l is
    2. A.
    zero
    B.
    independent of x
    C.
    proportional to x
    D.
    proportional to x2

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    Workspace

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    Answer : Option B

    Explanation :

    -NA-

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