Limit cycle oscillations of two-dimensional panels in low subsonic flow

Journal Article

Limit cycle oscillations of a two-dimensional panel in low subsonic flow have been studied theoretically and experimentally. The panel is clamped at its leading edge and free at its trailing edge. A structural non-linearity arises in both the bending stiffness and the mass inertia. Two-dimensional incompressible (linear) vortex lattice aerodynamic theory and a corresponding reduced order aerodynamic model were used to calculate the linear flutter boundary and also the limit cycle oscillations (that occur beyond the linear flutter boundary). © 2002 Published by Elsevier Science Ltd.

Full Text

Duke Authors

Cited Authors

  • Tang, D; Dowell, EH

Published Date

  • 2002

Published In

Volume / Issue

  • 37 / 7

Start / End Page

  • 1199 - 1209

International Standard Serial Number (ISSN)

  • 0020-7462

Digital Object Identifier (DOI)

  • 10.1016/S0020-7462(01)00140-8