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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

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