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Supersonic Flutter of a Cylindrical Panel in an Axi–Symmetric Mode

Published online by Cambridge University Press:  04 July 2016

D. J. Johns
D. J. Johns*
Affiliation:
College of Aeronautics
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Extract

In ref. 1 an extensive review was made of the panel flutter problem and analyses dealing with flutter of cylindrical shells of finite length were discussed in considerable detail. It was stated that one of the central points of controversy is in the choice of the appropriately simplified governing equations for the thin–walled elastic shell. Related to this is the choice of flutter mode and the question as to how the critical flutter speed depends upon the number of circumferential and axial waves in that mode.

Stepanov and Strack and Holt found that the critical Mach number decreases with increasing number of circumferential waves, and Fung has concluded that the axially symmetric mode is of the greatest interest.

The purpose of this note is to present a relatively simple analysis in which only axi–symmetric deformations of the shell are considered. The shell is assumed to be unreinforced longitudinally.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 64 , Issue 594 , June 1960 , pp. 362 - 363
Copyright
Copyright © Royal Aeronautical Society 1960

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References

1.Fung, Y. C. B. (1959). Panel Flutter. Agard Manual on Aeroelasticity, November 1959.Google Scholar
2.Stepanov, R. D. (1958). On the Flutter of Cylindrical Shells and Panels Moving in a Flow of Gas. N.A.C.A. T.M. 1438, September 1958.Google Scholar
3.Strack, S. L. and Holt, M. (1960). Supersonic Panel Flutter of a Cylindrical Shell of Finite Length. I.A.S. Paper No. 60-62, January 1960.Google Scholar
4.Timoshenko, S. (1936). Theory of Elastic Stability. McGraw Hill Co. 1936.Google Scholar
5.Johns, D. J. (1958). Some Panel Flutter Studies Using Piston Theory. Journal of the Aeronautical Sciences, Vol. 25, No. 11, pp. 679–684, November 1958.Google Scholar