Hostname: page-component-cd9895bd7-dzt6s Total loading time: 0 Render date: 2024-12-28T06:01:45.421Z Has data issue: false hasContentIssue false
  • English
  • Français

The glancing interaction of a Prandtl-Meyer expansion fan with a supersonic wake

Published online by Cambridge University Press:  04 July 2016

M. K. Smart  and
R. J. Stalker
M. K. Smart
Affiliation:
Department of Mechanical Engineering, University of Queensland, Australia
R. J. Stalker
Affiliation:
Department of Mechanical Engineering, University of Queensland, Australia
Get access Rights & Permissions [Opens in a new window]

Abstract

The glancing interaction of a Prandtl-Meyer expansion fan with a supersonic wake is examined. The particular supersonic wakes of interest are the combustion wake generated by a vertical strut injected scramjet, and the side wall boundary layer of a supersonic wind tunnel. A physical structure for the interaction is defined, and an approximate analysis of the downstream behaviour of the wake is presented. The phenomenon of wake over-turning by the glancing expansion fan is introduced, based on this analysis. This over-turning produces a high pressure zone on the expansion generating surface, which for the vertical strut injected scramjet, is part of the thrust nozzle. Combustion wake over-turning is suggested to be a major thrust producing mechanism in this form of scramjet.

Pressure measurements were taken on the expansion generating surface of a glancing interaction involving the side wall boundary layer of a small supersonic wind tunnel. Results from the analysis presented were found to be consistent with these measurements.

Type
Research Article
Information
The Aeronautical Journal , Volume 95 , Issue 942 , February 1991 , pp. 39 - 47
Copyright
Copyright © Royal Aeronautical Society 1991 

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 at WBM Pty Ltd, Brisbane, Australia

References

1. Stalker, R. J., Morgan, R. G. and Nettlefield, M. P. Wave processes in scramjet thrust generation, Combustion Flame, 1988, 71, pp 63–77.Google Scholar
2. Stalker, R. J. Sweepback effects in turbulent boundary layer-shock wave interactions, J Aero/Space Sci, May 1960, 27, pp 348–354.Google Scholar
3. Mee, D. J., Stalker, R. J. and Stollery, J. L. Glancinginteractions between single and intersecting oblique shock waves and a turbulent boundary layer, J Fluid Mech, 1987, 170, pp 411–433.Google Scholar
4. van dyke, M. D. First and second order theory of supersonic flow past bodies of revolution, J Aeronaut Sci, 1951,18, pp 161–169.Google Scholar
5. Lighthill, M. J. On boundary layers and upstream influence. II: Supersonic flows without separation, Proc R Soc A, 1953, 217, pp 487–501.Google Scholar
6. Winarto, H. and Stalker, R. J. Design parameters and performance of two-dimensional, asymmetric, ‘sliding block’, variable Mach number, supersonic nozzles, Aeronaut J, 1984, 88, (876) pp 270–280.Google Scholar
7. Smart, M. K. Analysis of a Scramjet Nozzle Exhaust, Master of Engineering Science Thesis, Department of Mechanical Engineering, University of Queensland, Brisbane, Australia. 1988.Google Scholar