Step Configuration Influence on Structure of Supersonic Reacting Flows in Channels with Sudden Expansion

  • N. N. Fedorova
  • Yu. V. Zakharova
  • M. A. Goldfeld
Conference paper


The study of supersonic turbulent flows in the channelswith sudden expansion (step/ cavities) is actual task since this configuration is used for ignition and flame stabilization. Supersonic combustion is studied for many years in order to support the future hypersonic flights. It well known that it is rather difficult to get the ignition and stable combustion at supersonic speeds [1]. The flow in the supersonic combustion chamber js charachterized by a short residence time which is only a few milliseconds of magnitude. A simple geometry to generate a flameholding region in supersonic flow is a backward facing step (BFS). Flows around BFS configuration were studied for decades and many papers were published regarding fundamental flow properties [2] as well as the scramjet combustion chamber utilization [3]. The effect of step configuration (“boattailing”) on the structure of compressible base flows was investigated in a numerous papers since Hama’s work [4]. Nevertheless, the question is little studied as far as supersonic chemically reacting flows in channels are concerned.


Reynolds Average Navier Stokes Recirculation Zone Bottom Wall Separation Zone Sudden Expansion 
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  1. 1.
    Curran, E.T., Heiser, W.H., Pratt, D.T.: Fluid Phenomena in Scramjet Combustion System. Annual Review of Fluid Mechanics 28, 323–360 (1996)CrossRefGoogle Scholar
  2. 2.
    Scherberg, M.G., Smith, H.E.: AIAA Journ. 5(1), 51–56 (1967)CrossRefGoogle Scholar
  3. 3.
    Uenishi, K., Rogers, R.C., Northam, G.B.: J. Propulsion 5(2), 158–164 (1989)CrossRefGoogle Scholar
  4. 4.
    Hama, F.R.: Experimental investigation of wedge base pressure and lip shock. TR 32-1033, Jet Propulsion Lab (1966)Google Scholar
  5. 5.
    Tien, J.H., Stalker, R.J.: Combustion and Flame 130, 329–348 (2002)CrossRefGoogle Scholar
  6. 6.
    Bedarev, I.A., Fedorov, A.V.: Combustion, Explosion, and Shock Waves 42(1), 19–26 (2006)CrossRefGoogle Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • N. N. Fedorova
    • 1
  • Yu. V. Zakharova
    • 2
  • M. A. Goldfeld
    • 2
  1. 1.Novosibirsk State University of Architecture and Civil Engineering (Sibstrin)NovosibirskRussia
  2. 2.Khristianovich Institute of Theoretical and Applied Mechanics SB RASNovosibirskRussia

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