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Shear Layer Evolution in Shock Wave Diffraction

  • B. W. Skews
  • C. Law
  • A. O. Muritala
  • S. Bode

Introduction

All previous studies on shock wave diffraction in shock tubes have spatial and temporal limitations due to the size of the test sections. These limitations result from either the reflection of the expansion wave, generated at the corner, from the top wall and/or of the reflection of the incident diffracted shock from the bottom wall of the test section passing back through the region of interest. This has limited the study of the evolution of the shear layer and its associated vortex which forms a relatively small region of the flow behind the shock and yet is a region of significant interest. A special shock tube is used in the current tests which allows evolution of the flow to be examined at a scale about an order of magnitude larger than in previously published results, with shear layer lengths of up to 250 mm being achieved. Tests were conducted at Mach numbers from 1.4 to 1.6 with wall angles of 10, 20, 30 and 90°

Keywords

Shock Wave Mach Number Shear Layer Test Section Shock Tube 
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.
    Skews, B.W.: J. Fluid Mech. 29, 705–719 (1967)CrossRefGoogle Scholar
  2. 2.
    Takayama, K., Inoue, O.: Shock Waves 1, 301–312 (1991)CrossRefGoogle Scholar
  3. 3.
    Sun, M., Takayama, K.: Shock Waves 13, 25–32 (2003)zbMATHCrossRefGoogle Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • B. W. Skews
    • 1
  • C. Law
    • 1
  • A. O. Muritala
    • 1
  • S. Bode
    • 1
  1. 1.Flow Research Unit, School of Mechanical, Industrial, and Aeronautical EngineeringUniversity of the WitwatersrandJohannesburgSouth Africa

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