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On the Conditions under which Energy can be Extracted from an Air Stream by an Oscillating Aerofoil

Published online by Cambridge University Press:  07 June 2016

N. C. Lambourne*
Affiliation:
Aerodynamics Division, National Physical Laboratory
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Summary

A simple system is considered in which a two-dimensional aerofoil in an air stream performs a coupled oscillation in pitching and vertical translation. An expression for the energy transferred from stream to aerofoil is derived as a function of the frequency parameter, amplitude ratio and phase difference, and the conditions under which positive energy can be extracted from the stream are investigated. The connection between the case of zero energy transfer, and the critical flutter state is noted.

Attention is confined to the incompressible case and diagrams show the results obtained when the air loads are obtained from (i) vortex sheet theory and (ii) the classical set of constant derivatives.

Vortex sheet theory leads to the conclusion that, provided that the amplitude ratio and phase difference satisfy certain conditions, energy can be extracted from the stream for all values of the frequency parameter. On the other hand, the use of a set of constant derivatives places an upper limit on the values of the frequency parameter for the extraction of energy.

Type
Research Article
Copyright
Copyright © Royal Aeronautical Society. 1954

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References

1. Lockspeiser, B. (1933). A Simple Approach to the Wing Flutter Problem. Journal of the Royal Aeronautical Society, July 1933.CrossRefGoogle Scholar
2. Kussner, H. G. (1935).The Present Stage of Development of the Problem of Wing Flutter. Luftfahrtforschung No. 6, October .1935.Google Scholar
3. Duncan, W. J. (1944). The Fundamentals of Flutter.A.R.C. Report 7716, 1944.Google Scholar
4. Greidanus, J. H.(1940).De Arbeid, die de Luchtkrachten per Tijdseenheid op een Trillenden Vleugel Verrichten en de Kritische Trillingsvormen van een Vlengel. Report V, 1237.National Aeronautical Research Institute, Amsterdam, 1940.Google Scholar
5. Frazer, R. A. (1939). On the Power Input required to Maintain Forced Oscillations of an Aeroplane Wing in Flight. R. & M. 1872, 1939.Google Scholar
6. Jones, W. P. (1942).Summary of Formulae and Notations used in Two Dimensional Derivative Theory. R. & M. 1958, 1942.Google Scholar
7. Biot, M. A. and Arnold,, Lee (1948). Low-speed Flutter and its Physical Interpretation. Journal of the Aeronautical Sciences, Vol. 15, No. 4, April 1948.Google Scholar
8. Duncan, W. J. and Collar, A. R. (1932). Present Position of Investigation of Airscrew Flutter. R. & M. 1518, 1932.Google Scholar
9. Williams, J. (1943). An Examination of Experimental Data relating to Flexural-torsional Wing Derivatives. R. & M. 1944, 1943.Google Scholar