Flutter/LCO suppression for high-aspect ratio wings


Journal Article

An experimental high-aspect ratio wing aeroelastic model with a device to provide a controllable slender body tip mass distribution has been constructed and the model response due to flutter and limit cycle oscillations has been measured in a wind tunnel test. A theoretical model has also 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 (an empirical extension of Theodorsen aerodynamic theory that accounts for flow separation). A dynamic perturbation analysis about a nonlinear static equilibrium is used to determine the small perturbation flutter boundary which is compared to the experimentally determined flutter velocity and flutter frequency. Time simulation is used to compute the limit cycle oscillations response when the flutter/LCO control system is ON or OFF. Theory and experiment are in good agreement for predicting the flutter/LCO suppression that can be achieved with the control device.

Full Text

Duke Authors

Cited Authors

  • Tang, D; Dowell, EH

Published Date

  • January 1, 2009

Published In

Volume / Issue

  • 113 / 1144

Start / End Page

  • 409 - 416

International Standard Serial Number (ISSN)

  • 0001-9240

Digital Object Identifier (DOI)

  • 10.1017/S0001924000003079

Citation Source

  • Scopus