Hostname: page-component-586b7cd67f-tf8b9 Total loading time: 0 Render date: 2024-11-24T11:32:45.293Z Has data issue: false hasContentIssue false
  • English
  • Français

The Three-Dimensional Interaction of a Shock Wave with a Turbulent Boundary Layer

Published online by Cambridge University Press:  07 June 2016

A. McCabe
A. McCabe*
Affiliation:
The Mechanics of Fluids Department, University of Manchester
Get access

Summary

Experiments are described on the interaction of the shock wave generated by a wedge in a supersonic wind tunnel with the turbulent boundary layer on the side wall. It is shown that the onset of separation appears to be largely affected by the action of streamwise vorticity in the interaction region. A simple approximate theory based on this concept shows reasonable agreement with the experimental results. Comparisons have been made with two-dimensional interactions of normal shocks and boundary layers, but they did not produce any conclusive results.

Type
Research Article
Information
Aeronautical Quarterly , Volume 17 , Issue 3 , August 1966 , pp. 231 - 252
Copyright
Copyright © Royal Aeronautical Society. 1966

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. Gadd, G. E. Interactions between shock waves and boundary layers. Proceedings of a Symposium on Boundary Layer Research, Freiburg, 1957.Google Scholar
2. Stalker, R. J. Sweepback effects in turbulent boundary-layer shock-wave interaction. Journal of the Aerospace Sciences, Vol. 27, p. 348, May 1960.Google Scholar
3. Stanbrook, A. An experimental study of the glancing interaction between a shock wave and a turbulent boundary layer. ARC Current Paper 555, 1960.Google Scholar
4. Stanbrook, A. The surface oil flow technique used in high speed wind tunnels. RAE Tech. Note Aero. 2712, 1960.Google Scholar
5. Maskell, E. C. Flow separation in three dimensions. RAE Report Aero. 2565, 1955.Google Scholar
6. Gadd, G. E. Interactions between normal shock waves and turbulent boundary layers. ARC R& M 3262, 1962.Google Scholar
7. Seddon, J. The flow produced by interaction of a turbulent boundary layer with a normal shock wave of sufficient strength to cause separation. Paper presented at the AGARD Boundary Layer Meeting, London, 1960.Google Scholar