Limit-cycle hysteresis response for a high-aspect-ratio wing model


Journal Article

An experimental high-aspect-ratio wing aeroelastic model with a slender body at the tip has been constructed, and the response due to flutter and limit-cycle oscillations (LCOs) has been measured in a wind-tunnel test. A theoretical model has been developed and calculations made to correlate with the experimental data. Structural equations of motion based on nonlinear beam theory are combined with the ONERA aerodynamic stall model to study the LCO hysteresis phenomenon of a high-aspect-ratio wing model. Time simulation and a harmonic balance approach are each used to compute the LCO hysteretic response. The results between the theory and experiment are in good agreement.

Full Text

Duke Authors

Cited Authors

  • Tang, D; Dowell, EH

Published Date

  • January 1, 2002

Published In

Volume / Issue

  • 39 / 5

Start / End Page

  • 885 - 888

International Standard Serial Number (ISSN)

  • 0021-8669

Digital Object Identifier (DOI)

  • 10.2514/2.3009

Citation Source

  • Scopus