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Shock Waves pp 479-485 | Cite as

Study of separated flows over double wedges and cones

  • T. Hashimoto
  • K. Takayama
Conference paper

Abstract

This paper reports results of flow diagnostics over a double wedge or cone at a stagnation enthalpy 4.8 MJ/kg. The experiment was carried out in a free piston shock tunnel at Interdisciplinary Shock Wave Research Center (ISWRC) at a nominal Mach number of 6.99. Schlieren and double exposure holographic interferometry were applied to visualize the flow fields. The flow fields induced separation over double wedge or cone were successfully visualized.

Keywords

Separation Zone Wedge Angle Oblique Shock Double Cone Shock Interaction 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

  1. 1.
    B. Edney: Anomalous heat transfer and pressure distributions on blunt bodies at hypersonic speeds in the presence of an impinging shock. FFA Rep. 115 (1968)Google Scholar
  2. 2.
    J. Olejniczak: Computational and Experimental Study of Nonequilibrium Chemistry in Hypersonic Flows. Ph. D. Thesis, University of Minnesota (1997)Google Scholar
  3. 3.
    K. Koremoto: Optimization of the Characteristics of a Free Piston Shock Tunnel. PhD Thesis, Tohoku University, (in Japanese) (1999)Google Scholar
  4. 4.
    T. Hashimoto: Analytical and Experimental Study of Hypersonic Nozzle Flows in Free Piston Shock Tunnel. PhD Thesis, Tohoku University (2003)Google Scholar
  5. 5.
    J.A. Lordi, R.E. Mates, J.R. Moselle: Computer program for the numerical solution of nonequilibrium expansions of reacting gas mixtures. NASA CR-472 (1959)Google Scholar
  6. 6.
    K. Takayama: Application of holographic interferometry to shock wave research. Proc. of the Society of Photo-Optical Instrumentation Engineers 398, 174 (1983)ADSGoogle Scholar

Copyright information

© Tsinghua University Press and Springer-Verlag Berlin Heidelberg 2005

Authors and Affiliations

  • T. Hashimoto
    • 1
  • K. Takayama
    • 2
  1. 1.Japan Aerospace Exploration AgencyKakuda, MiyagiJapan
  2. 2.Interdisciplinary Shock Wave Research Center, Institute of Fluid ScienceTohoku UniversitySendai, MiyagiJapan

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