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

  • M. K. Smart (a1) and R. J. Stalker (a1)

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.

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References

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1. Stalker, R. J., Morgan, R. G. and Nettlefield, M. P. Wave processes in scramjet thrust generation, Combustion Flame, 1988, 71, pp 6377.
2. Stalker, R. J. Sweepback effects in turbulent boundary layer-shock wave interactions, J Aero/Space Sci, May 1960, 27, pp 348354.
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 411433.
4. van dyke, M. D. First and second order theory of supersonic flow past bodies of revolution, J Aeronaut Sci, 1951,18, pp 161169.
5. Lighthill, M. J. On boundary layers and upstream influence. II: Supersonic flows without separation, Proc R Soc A, 1953, 217, pp 487501.
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 270280.
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.

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

  • M. K. Smart (a1) and R. J. Stalker (a1)

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