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Experimental investigation of the turbulent boundary layer at high Reynolds numbers and a Mach number of 0·8

Published online by Cambridge University Press:  04 July 2016

L. Gaudet
L. Gaudet*
Affiliation:
Royal Aircraft Establishment, Bedford
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Summary

Measurements of the turbulent boundary layer on a sidewall of the RAE 8 ft × 8 ft wind tunnel are described. Velocity profiles and wall shear-stress measurements were obtained for a Mach number of 0·8 over a Reynolds number range of over a decade up to a value of nearly 400 million.

A skin-friction relationship is deduced together with a description of the velocity profile and boundary-layer growth based upon the velocity-defect law using kinematic parameters for constant-pressure flows without heat transfer.

Previous data for Mach numbers up to 2·8 obtained in the same tunnel are shown to be well matched with the present analysis and the use of simple scaling factors for compressible flows is confirmed.

Type
Research Article
Information
The Aeronautical Journal , Volume 90 , Issue 893 , March 1986 , pp. 83 - 94
Copyright
Copyright © Royal Aeronautical Society 1986 

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References

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