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The effect of backlash and trailing-edge strips on the flutter speed of a two-dimensional model of a tailplane with tab

Published online by Cambridge University Press:  04 July 2016

Betty Emslie  and
A. Goldman
Betty Emslie
Affiliation:
Structures Division Aeronautical Research Laboratories Melbourne, Australia
A. Goldman
Affiliation:
Structures Division Aeronautical Research Laboratories Melbourne, Australia
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Summary

The effect of backlash and trailing-edge strips on the flutter speed of a two-dimensional model of a tailplane with tab has been investigated in a series of wind tunnel tests. When backlash is present, a change in preload, which is achieved by varying the incidence of the tab, can dramatically alter the flutter speed. The addition of trailing-edge strips to the tab lowered the flutter speed.

Type
Research Article
Information
The Aeronautical Journal , Volume 86 , Issue 859 , November 1982 , pp. 337 - 340
Copyright
Copyright © Royal Aeronautical Society 1982 

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References

1. Report on investigation of tailplane flutter GAF N24 Nomad Aircraft at Avalon, Victoria on 6th August 1976. Dept. of Transport, Australia. Special Investigation Report 77–1.Google Scholar
2. Woolston, D. S., Runyan, H. L. and Byrdsong, T. A. Some effects of system non-linearities in the problem of aircraft flutter. NACA TN 3539, October 1955.Google Scholar
3. Long, G. and Farrell, P. A. The effect of trailing-edge strips on the unsteady aerodynamic forces on a control surface. The Aeronautical Journal, November 1980, 84, 388.Google Scholar
4. Broadbent, E. G. The elementary theory of aeroelasticity. Aircraft Engineering, March-June 1954.Google Scholar