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Flutter/LCO suppression for high-aspect ratio wings

Published online by Cambridge University Press:  03 February 2016

D. Tang  and
E. H. Dowell
D. Tang
Affiliation:
demant@duke.edu, Department of Mechanical Engineering and Materials Science, Duke University Durham, NC, USA
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Abstract

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.

Type
Research Article
Information
The Aeronautical Journal , Volume 113 , Issue 1144: Flight structures fundamental research in the United States of America: A Special Issue , June 2009 , pp. 409 - 416
Copyright
Copyright © Royal Aeronautical Society 2009 

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