It is shown that activation of the trailing-edge control of an airfoil leads to single-degree-of-freedom type instabilities which span over a very wide region of reduced frequencies k, including high values of k (unlike the nonactivated system). These instabilities are shown to be sensitive to changes in pitching axis location, control deflection phase angle, and values of the reduced frequency. These sensitivities of the single-degree-of-freedom system cause the activated airfoil to be potentially sensitive to changes in flight conditions, and may be the source of the many difficulties encountered in suppressing classical multi-degree-of-freedom flutter by means of active controls. The results presented herein relate to zero Mach number and to a 20% trailing-edge control surface.


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    Title :

    On single-degree-of-freedom flutter induced by activated controls


    Contributors:
    Nissim, E. (author) / Lottati, I. (author)


    Publication date :

    1979-10-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English







    Transonic Single-Degree-of-Freedom Flutter and Natural Mode Instabilities

    Bendiksen, O.O. / American Institute of Aeronautics and Astronautics; American Society of Mechanical Engineers; American Society of Civil Engineers | British Library Conference Proceedings | 2013