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

E. Nissim, I. Lottati

Research output: Contribution to journalArticlepeer-review


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 A, 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.

Original languageEnglish
Pages (from-to)402-406
Number of pages5
JournalJournal of Guidance, Control, and Dynamics
Issue number5
StatePublished - 1979
Externally publishedYes


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