Hostname: page-component-78c5997874-lj6df Total loading time: 0 Render date: 2024-11-15T02:12:28.109Z Has data issue: false hasContentIssue false
  • English
  • Français

Calculation of two-dimensional and three-dimensional regular shock intersections

Published online by Cambridge University Press:  04 July 2016

B. L. Hunt
B. L. Hunt*
Affiliation:
Department of Aeronautical Engineering, University of Bristol
Get access Rights & Permissions [Opens in a new window]

Extract

The intersection of two oblique shock waves of opposite families is a common occurrence in supersonic flows. It can result either in a regular intersection, where the downstream waves are weak shocks and a single slip line emanates from the intersection, or in a form of Mach reflection where a strong shock bridges the gap between two three-shock confluences each of which generates a slip line. The transition between regular and Mach reflection has been discussed for the symmetrical case by Henderson and Lozzi and by Horning et al. The conditions at a three-shock confluence point have been analysed for two-dimensional flow by Henderson and for three-dimensional flow by Hunt and Lamont and by Rudman.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 84 , Issue 836 , September 1980 , pp. 285 - 289
Copyright
Copyright © Royal Aeronautical Society 1980 

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

*

Now Manager, Propulsion Research, Northrop Corporation, Hawthorne, California.

References

1. Henderson, L. F. and Lozzi, A. Experiments on transition of Mach reflexion. Journal of Fluid Mechanics, Vol 68, p 139, 1975.Google Scholar
2. Hornung, H. G., Oertel, H. and Sandeman, R. J. Transition to Mach reflection of shock waves in steady and pseudosteady flow with and without relaxation. Journal of Fluid Mechanics, Vol 90, p 541, 1979.Google Scholar
3. Henderson, L. F. On the confluence of three shock waves in a perfect gas. Aeronautical Quarterly, Vol XV, p 181, May 1964.Google Scholar
4. Henderson, L. F. The three shock confluence on a simple wedge intake. Aeronautical Quarterly, Vol XVI, p 42, February 1965.Google Scholar
5. Hunt, B. L. and Lamont, P. J. The confluence of three shock waves in three-dimensional flow. Aeronautical Quarterly, Vol XXIX, p 18, February 1978.Google Scholar
6. Rudman, S. Three-dimensional shock wave interactions. AIAA Paper 79-0137, 1979.Google Scholar
7. Henderson, L. F. On a class of multi-shock interactions in a perfect gas. Aeronautical Quarterly, Vol XVII, p 1, February 1966.Google Scholar