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Discussion :: GATE Aeronautical Engineering

  1. Consider an airplane with rectangular straight wing at dihedral angle T = 100 . Lift curve slope of wing airfoil section (constant over the whole span of the wing) is cla = 5.4/rad. The roll stability derivative, Clb in per radian is __________
    2. A.
    0.25 to 0.26
    B.
    -0.25 to -0.26
    C.
    0.23 to 0.24
    D.
    -0.23 to -0.24

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    Answer : Option D

    Explanation :

    -NA-

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