Limit Cycle Oscillations of a Cantilevered Wing in Low Subsonic Flow

Published

Journal Article

A nonlinear, aeroelaslic analysis of a low-aspect, rectangular wing modeled as a plate of constant thickness demonstrates that limit cycle oscillations of the order of the plate thickness are possible. The structural nonlinearity arises from double bending in both the chordwise and spanwise directions. The present results using a vortex lattice aerodynamic model for low-Mach-number flows complement earlier studies for high supersonic speed that showed similar qualitative results. Also, the theoretical results are consistent with experimental data reported by other investigators for low-aspect-ratio delta wings.

Duke Authors

Cited Authors

  • Tang, D; Dowell, EH; Hall, KC

Published Date

  • March 1, 1999

Published In

Volume / Issue

  • 37 / 2-3

Start / End Page

  • 364 - 371

International Standard Serial Number (ISSN)

  • 0001-1452

Citation Source

  • Scopus