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Transonic Buffeting on Aerofoils*

Published online by Cambridge University Press:  04 July 2016

C. J. Wood
C. J. Wood*
Affiliation:
Imperial College of Science and Technology
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Extract

There are many problems to be solved when it is required to fly an aircraft at speeds approaching the speed of sound. When the speed of the aeroplane exceeds its critical Mach number, regions of supersonic flow appear at points on its surface, where the velocity of the displaced air is greatest. These regions of supersonic flow increase in size with increasing speed until the flow is wholly supersonic. The range of speed in which this mixed flow occurs is called the transonic range. In this range an aircraft will experience a sudden increase in drag, trim changes, loss of control effectiveness and possibly instability, or buffeting.

Type
Research Article
Information
The Aeronautical Journal , Volume 64 , Issue 599 , November 1960 , pp. 683 - 686
Copyright
Copyright © Royal Aeronautical Society 1960

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Footnotes

*

Read before the Brough Branch in April 1959 and awarded the 1960 N. E. Rowe Medal for the 21-26 years of age group

References

1.Pearcey, H. H. (1955). Some Effects of Shock Induced Separation of Turbulent Boundary Layers in Transonic Flow past Aerofoils. C.C.274, June 1955.Google Scholar
2.Young, A. D. and Winterbottom, N. E. (1950). Note on the Effects of Compressibility on the Profile Drag of Aerofoils at Subsonic Mach Numbers in the Absence of Shock Waves. R. & M. 2400, 1950.Google Scholar
3.Sinnott, C. S. (1957). On the How of a Sonic Stream Past an Aerofoil Surface. A.R.C. 19169, 1957.Google Scholar
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5.Chinneck, A., Jones, G. C. A. and Tracey, C. M. (1955). Blowing at Transonic Speeds. A.R.C. 17564, 1955.Google Scholar