Hostname: page-component-cd9895bd7-q99xh Total loading time: 0 Render date: 2024-12-28T22:07:39.264Z Has data issue: false hasContentIssue false
  • English
  • Français

Oblique shock wave—turbulent boundary layer interaction with suction

Published online by Cambridge University Press:  04 July 2016

D. B. Lee  and
R. Leblanc
D. B. Lee
Affiliation:
Centre d’Etudes Aérodynamiques et Thermiques, University of Poitiers, Poitiers, France
R. Leblanc
Affiliation:
Centre d’Etudes Aérodynamiques et Thermiques, University of Poitiers, Poitiers, France
Get access Rights & Permissions [Opens in a new window]

Abstract

The interaction of an incident oblique shock wave with the turbulent boundary layer with suction is investigated. Wall streamline and schlieren photograph visualisations as well as the pressure measurements on the wall are made. Boundary layer surveys with pressure probes and hot-wire probes are also done. The suction downstream of the interaction almost nullifies the shock reflection while the higher suction up and downstream of the interaction results in a reflection similar to that in inviscid flow.

Type
Research Article
Information
The Aeronautical Journal , Volume 88 , Issue 879 , November 1984 , pp. 416 - 427
Copyright
Copyright © Royal Aeronautical Society 1984 

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.)

Footnotes

*

Present address: Korean Institute of Aeronautical Technology, Seoul.

References

1. Allen, H. J. Transonic wind tunnel development of the NACA, AGARD memorandum AG17/P7. 1954.Google Scholar
2. Fournier, J., Leblanc, R. and Vayssaire, J. C. Application des parois perméables aux veines de souffleries transsoniques, 12ème Colloque AAAF, Poitiers. 1975.Google Scholar
3. Lee, D. B. Etude de l’intéraction onde de choc-couche limite turbulente sur parol poreuse avec aspiration, Dr Ing Thesis, Univ of Poitiers, Poitiers. 1983.Google Scholar
4. Tassa, Y. and Sankar, N. L. Effect of suction on a shock-separated boundary layer. A numerical study, AIAA Journal, 1979,17,1268–1270.Google Scholar
5. Inger, G. R. and Zee, G. Transonic shock wave/turbulent-boundary-layer interaction with suction and blowing, J Aircraft, 1978, 15,750–754.Google Scholar
6. Seebaugh, W. R. and Childs, M. E. An experimental study of the interaction of conical wave and a turbulent boundary layer including suction effects, AIAA paper No 69-450. 1969.Google Scholar
7. Wong, W. F. The application of boundary layer suction to suppress strong shock-induced separation in supersonic inlets, AIAA paper No. 74-1063,1974.Google Scholar
8. Mathews, D. C, Childs, M. E. and Paynter, G. C. Use of Cole’s universal wake function for compressible turbulent boundary layers, J Aircraft, 1970,7,137–140.Google Scholar
9. Spalding, D. B. and Chi, S. W. The drag of a compressible boundary layer on a smooth flat plate with and without heat transfer, J Fluid Mech 1963,18,117–143.Google Scholar
10. Cebeci, T. and Smith, A. M. O. Analysis of turbulent boundary layers, Academic Press, New York, 1974.Google Scholar
11. Baker, R. J. and Launder, B. E. The turbulent boundary layer with foreign gas injection — I. Measurements in zero pressure gradient, Int J Heat Mass Transfer. 1974,17,275–291.Google Scholar
12. Squire, L. C. A law of the wall for compressible turbulent boundary layers with air injection, J Fluid Mech, 1963, 37, 449–458.Google Scholar
13. Ardonceau, P., Alziary, T., Lee, D. H. and Goethals, R. Turbulence behaviour in a shock wave/boundary layer inter action, AGARD CP-271,1979.Google Scholar
14. Alemdaroglu, N. Etudes, mise au point et traitement numérique des mesures aérodynamiques d’une soufflerie anechoique, Dr Ing Thesis, Univ of Poitiers, Poitiers. 1979.Google Scholar
15. Green, J. E. Reflection of an oblique shock wave by a turbulent boundary layer, J Fluid Mech, 1970,40,81–85.Google Scholar
16. Henserson, L. F. The reflection of a shock wave at a rigid wall in the pressure of a boundary layer, J Fluid Mech. 1967, 30, 699–722.Google Scholar
17. Squire, L. C. and Smith, M. J. Interaction of a shock wave with a turbulent boundary layer disturbed by injection, Aero Quarterly. 1980,31,85–112.Google Scholar