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Recent studies of the occurrence of post-flutter limit cycle oscillations (LCO) of the F-16 have provided good support to the long-standing hypothesis that this phenomenon involves a nonlinear structural damping.

Recent studies of the occurrence of post-flutter limit cycle oscillations (LCO) of the F-16 have provided good support to the long-standing hypothesis that this phenomenon involves a nonlinear structural damping. A potential mechanism for the appearance of nonlinearity in the damping are the nonlinear geometric effects that arise when the deformations become large enough to exceed the linear regime.

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    Date Created
    • 2015
    Resource Type
  • Text
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    • Partial requirement for: M.S., Arizona State University, 2015
      Note type
      thesis
    • Includes bibliographical references (pages 69-71)
      Note type
      bibliography
    • Field of study: Mechanical engineering

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    by Pengchao Song

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