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Some Boundary Layer Measurements on a Slender Wing at Supersonic Speeds

Published online by Cambridge University Press:  04 July 2016

R. T. Griffiths
R. T. Griffiths*
Affiliation:
Formerly Royal Aircraft Establishment, Bedford, now Lecturer in Mechanical Engineering, University College, Swansea
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Summary

Boundary layer measurements have been made at four positions on a slender gothic wing of aspect ratio 0·75. Test's were made over a range of incidence at M=1·42 and 1·82. With transition fixed by roughness near the leading edge the boundary layer thickness varied little with small positive or negative incidence but was reduced at larger incidences, this being most marked at positive incidence for positions nearest the leading edge due to the influence of the wing vortex. With the exception of positions in the vicinity of the vortex, a good estimate of the boundary layer thickness was given by the theory for incompressible flow over a flat plate and an excellent estimate of the variation of local static pressure and Mach number with incidence was given by not-so-slender wing theory.

Type
Research Article
Information
The Aeronautical Journal , Volume 67 , Issue 629 , May 1963 , pp. 291 - 295
Copyright
Copyright © Royal Aeronautical Society 1963

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References

1.Squire, L. C. An Experimental Investigation at Supersonic Speeds of the Characteristics of Two Gothic Wings, One Plane and One Cambered. ARC, R & M 3211, July 1960.Google Scholar
2.Monaghan, R. J. The Use of Pitot Tubes in the Measurement of Laminar Boundary Layers in Supersonic Flow. ARC, R & M 3056, May 1955.Google Scholar
3.Davies, F. V. Some Effects of Pitot Size on the Measurements of Boundary Layers in Supersonic Flow. Unpublished M of A Report ARC 15430, August 1952.Google Scholar
4.Piercy, N. A. V.Aerodynamics. The English Universities Press Ltd.Google Scholar
5.Jones, R. T. Properties of Low Aspect Ratio Pointed Wings at Speeds Below and Above the Speed of Sound. NACA Report 835, 1946.Google Scholar
6.Adams, Mac. C. and Sears, W. R.Journal of the Aeronautical Sciences, Vol. 20, p. 85, February 1953.Google Scholar
7.Squire, L. C. Some Applications of “Not-So-Slender” Wing Theory to Wings with Curved Leading Edges. ARC, R & M 3278, July 1960.Google Scholar