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Shock Waves pp 695-700 | Cite as

Investigation of supersonic/hypersonic shock-wave/boundary-layer interactions (SBLIs)

  • R. O. Bura
  • G. T. Roberts
  • Y. F. Yao
  • N. D. Sandham
Conference paper

Abstract

Numerical simulations of supersonic/hypersonic laminar shock-wave/boundary-layer interactions (SBLIs) have been carried out by solving the Navier-Stokes (NS) equations using a compressible flow code over a wide range of Mach number, Reynolds number and shock strength. The results were analysed by means of correlation laws, simplified theoretical analysis, and comparison with experiments. The analysis confirmed that the flow properties in the vicinity of the separation point conformed to the free interaction concept, in agreement with other investigators. The correlation of separation length, which included the viscous interaction parameter, \( \bar \chi \), revealed different constants obtained at supersonic and hypersonic speed. The comparisons showed that the experimental results exhibited a higher heating rate than predicted by laminar SBLI simulations, possibly caused by free shear layers transition.

Keywords

Reynolds Number Mach Number Incident Shock Separation Point Separation Bubble 
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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Copyright information

© Tsinghua University Press and Springer-Verlag Berlin Heidelberg 2005

Authors and Affiliations

  • R. O. Bura
    • 1
  • G. T. Roberts
    • 1
  • Y. F. Yao
    • 1
  • N. D. Sandham
    • 1
  1. 1.Aerodynamics and Flight Mechanics Research Group, School of Engineering Sciences, Aerospace EngineeringUniversity of SouthamptonHantsUK

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