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


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.


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.


Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.


  1. 1.
    R.O. Bura, G.T. Roberts, N.D. Sandham and Y.F. Yao: ‘Simulation of Hypersonic Shock-wave/Boundary-Layer Interactions’. In: Proc. of 23rd Int. Symp. on Shock Waves (ISSW23). Forth Worth, Texas, USA, July 21–27, 2001 Google Scholar
  2. 2.
    Y.F. Yao, R.O. Bura, N.D. Sandham and G.T. Roberts: ‘Time-Accurate Simulation of Supersonic and Hypersonic Laminar Shock/Boundary-Layer Interactions’. In: Proc. of CE AS Aerospace Aerodynamics Research Conference, Cambridge, United Kingdom, June 10–13, 2002 Google Scholar
  3. 3.
    N.D. Sandham, Q. Li and H.C. Yee: Entropy splitting for high-order numerical simulation of compressible turbulence. J. of Computational Physics 178, 307 (2002)ADSCrossRefGoogle Scholar
  4. 4.
    D.R. Chapman and D.M Kuehn and H.K. Larson: Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition. NACA Report 1356 (1958)Google Scholar
  5. 5.
    E. Katzer: On the lengthscale of laminar shock/boundary-layer interaction. J. of Fluid Mechanics 206, 477 (1989)ADSCrossRefGoogle Scholar
  6. 6.
    L.G Kaufman II and C. B. Johnson: Weak incident shock interactions with Mach 8 laminar boundary-layers. NASA TN D-7835 (1974)Google Scholar
  7. 7.
    F.T. Hung and D.O. Barnett: Shock wave-boundary layer interference heating analysis. AIAA Paper 73-0238 (1973)Google Scholar
  8. 8.
    J.D. Anderson: Hypersonic and High Temperature Gas Dynamics. (McGraw-Hill, Inc. 1989)Google Scholar
  9. 9.
    E.R.G. Eckert: Engineering relations for skin friction and heat transfer to surfaces in high velocity flows. Journal of the Aeronautical Sciences 22, 585 (1955)zbMATHGoogle Scholar
  10. 10.
    Y.F. Yao and N.D. Sandham: ‘Direct Simulation of Transitional Shock Boundary-Layer Interactions at Mach 2’. In: Proc. of 2nd International Conference on Computational Fluid Dynamics, Sydney, Australia, July 15–19, 2002 Google Scholar

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

Personalised recommendations