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Method for Providing Warning of the Onset of Buffeting, Stalling and Other Undesirable Effects of Flow Separation

Published online by Cambridge University Press:  04 July 2016

D. W Holder  and
H. H. Pearcey
D. W Holder
Affiliation:
Aerodynamics Division, National Physical Laboratory
H. H. Pearcey
Affiliation:
Aerodynamics Division, National Physical Laboratory
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Extract

A Method is described for providing warning of the onset of undesirable effects produced by flow separation on an aircraft wing. It is based on static pressure measurements near the trailing edge and appears to have advantages over alternative methods.

Recent work has suggested that certain effects of flow separation such as buffeting, aileron buzz and undesirable changes in loading, occur when a “ bubble ” of separated flow originating at the leading edge of a wing, or at a shock wave on its surface, first becomes sufficiently large to affect the flow at the trailing edge.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 62 , Issue 573 , September 1958 , pp. 674 - 676
Copyright
Copyright © Royal Aeronautical Society 1958

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References

1. Holder, D. W., Pearcey, H. H., Gadd, G. E. and Seddon, J. (1954). The Interaction between Shock Waves and Boundary Layers. (With a note on “The Effects of the Interaction on the Performance of Supersonic Intakes.”) C.P.I80, February 1954.Google Scholar
2. Pearcey, H. H. (1955). Some Effects of Shock-Induced Separation of Turbulent Boundary Layers in Transonic Flow past Aerofoils. Paper 9 presented at the Symposium on Boundary Layer Effects in Aerodynamics at the National Physical Laboratory, Teddington, Middlesex, 31st March- 2nd April 1955. A.R.C. R. & M. 3108, June 1955.Google Scholar
3. Pearcey, H. H. (1955). The Occurrence and Development of Boundary Layer Separations at High Incidences and High Speeds. A.R.C. R. & M. 3109, September 1955.Google Scholar
4. Duddy, R. R. (1955). Some Comparisons between Wind Tunnel Model and Flight-Test Results on Aircraft at High Angles of Attack. AGARD Paper presented at the Joint Session of the Flight Test Techniques and Wind Tunnel and Model Testing Panels, Ottawa, 1955 (AG18/P8).Google Scholar