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Thickness Parameters by Rapid Integration of Turbulent Boundary Layer Profiles*

Published online by Cambridge University Press:  28 July 2016

H. C. Garner
H. C. Garner*
Affiliation:
National Physical Laboratory
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Extract

The turbulent boundary layer on an aerofoil is represented by simple distributions of velocity, so as to obtain approximate general formulae for the displacement and momentum thicknesses in terms of two ratios of local velocity to that at the edge of the boundary layer.

Optimum positions for the local velocity are calculated to be at 0·15 and 0·62 of the boundary layer thickness from the aerofoil surface. The accuracy of the formulae is closely examined. A rapid experimental and numerical procedure is given for estimating the displacement and momentum thicknesses within ± 2 per cent. A minimum of seven velocity measurements has been found satisfactory in practice.

Information

Type
Technical Notes
Information
The Aeronautical Journal , Volume 61 , Issue 556 , April 1957, pp. 278 - 281
Copyright
Copyright © Royal Aeronautical Society 1957

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Footnotes

*

The work described in this Note was carried out in the Aerodynamics Division of the National Physical Laboratory, and it is published on the recommendation of the Aeronautical Research Council and by permission of the Director of the Laboratory.

References

1. von Doenhoff, A. E. and Tetervin, N. (1943). Determination of General Relations for the Behaviour of Turbulent Boundary Layers. N.A.C.A. Report No. 772, April 1943.Google Scholar
2. Klebanoff, P. S. and Diehl, Z. W. (1951). Some Features of Artificially Thickened Fully Developed Turbulent Boundary Layers with Zero Pressure Gradient. N.A.C.A. Report No. 1110, October 1951.Google Scholar
3. Bryer, D. W., Walshe, D. E. and Garner, H. C. (1955). Pressure Probes Selected for Mean-Flow Measurements. Exploration of Turbulent Boundary Layers. A.R.C. Report 17997, November 1955. To appear as R. and M. No. 3037.Google Scholar