Hostname: page-component-cd9895bd7-dzt6s Total loading time: 0 Render date: 2024-12-25T07:34:40.534Z Has data issue: false hasContentIssue false
  • English
  • Français

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
Get access Rights & Permissions [Opens in a new window]

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 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Winter, K. G. and Gaudet, L. Turbulent boundary-layer studies at high Reynolds numbers at Mach numbers between 0·2 and 2·8. R&M 3712, December 1970.Google Scholar
2. Gaudet, L. Experimental investigation of the turbulent boundary layer at high Reynolds numbers and a Mach number of 0·8. RAE TR 84094, 1984.Google Scholar
3. De Brederode, V. and Bradshaw, P. A note on the empirical constants appearing in the logarithmic law for turbulent flows. Imperial College Report 74-03, 1974.Google Scholar
4. Coles, D. E. The turbulent boundary layer in a compressible fluid. Rand Rpt R-403-PR, September 1962.Google Scholar
5. Spalding, D. B. and Chi, S. W. The drag of a compressible turbulent boundary layer on a smooth plate with and without heat transfer. J Fluid Mech, 1964, 18, Part 1. 117–143.Google Scholar
6. Fernholz, H. A new empirical relationship between the formparameters H 32 and H 12 in boundary-layer theory. J Roy AeroSoc, September 1962, 66, 588–589.Google Scholar
7. Wieghardt, K. Turbulente Reibungsschichten Göttinger. Monographien B5, 1945.Google Scholar
8. East, L. F., Sawyer, W. G., and Nash, C. R. An investigation of the structure of equilibrium turbulent boundary layers. RAE Technical Report 79040, 1979.Google Scholar
9. Green, J. E., Weeks, D. J. and Brooman, J. F. W. Prediction of turbulent boundary layers and wakes in compressible flow by a lag-entrainment method. ARC R&M No. 3791, 1977.Google Scholar
10. Winter, K. G. Methods used in setting the 8 ft x 8 ft wind tunnel variable supersonic nozzles. RAE Technical Note Aero 2912, 1963.Google Scholar
11. Smith, K. G. and Winter, K. G. Boundary-layer growth on the nozzles of the RAE 8 ft x 8 ft supersonic wind tunnel. RAE Technical Note Aero 2767, 1961.Google Scholar
12. Bradshaw, P. Ferriss, D. H. and Atwell, N. P. Calculation of turbulent boundary layers using the turbulent energy equation. J Fluid Mech, 1967. 28, Part 3.Google Scholar
13. McMillan, F. A. Viscous effects on pitot tubes at low speeds. ARC 16866, FM 2081, 1954.Google Scholar