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Stability of thin Viscous Shock Layer on a Wedge in Hypersonic Flow of a Perfect Gas

  • G. V. Petrov
Part of the International Union of Theoretical and Applied Mechanics book series (IUTAM)

Summary

In hypersonic flows the boundary layer thickness can be not small compared to the shock layer thickness, disturbances originated inside of the boundary layer, therefore, can not attenuate over the inviscid part of the shock layer so much that their reflection from the leading-edge shock wave can be left out of account. In this work the condition of propagation only inside of the shock layer, and linearized Rankine-Hugoniot conditions at the shock wave are imposed on disturbances or their inviscid components. The second mode instability for a flat plate takes as a starting point of the numerical study. There were discovered a series of branch and saddle points of the dispersion relation as well as absolute instability.

Keywords

Shock Wave Saddle Point Flat Plate Shock Layer Hypersonic Flow 
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.
    Hayes, W.D.; Probstein, R.F.: Hypersonic flow theory. Second ed., vol. 1, Inviscid flow. N.-Y, London: Academic press 1966.Google Scholar
  2. 2.
    Mack, L.M.: Boundary layer stability theory. Doc. 900–277, Rev. A. Pasadena: JPL 1969.Google Scholar
  3. 3.
    Dunn, D.W.; Lin, C.C.: On the stability of the laminar boundary layer in a compressible fluid. J. Aeron. Sci. 22, N 7 (1969).Google Scholar
  4. 4.
    De Bruijn, N.G.: Asymptotic methods in analysis. Amsterdam, Groningen 1958.MATHGoogle Scholar

Copyright information

© Springer-Verlag, Berlin, Heidelberg 1985

Authors and Affiliations

  • G. V. Petrov
    • 1
  1. 1.Institute of Theoretical and Applied MechanicsUSSR Academy of SciencesNovosibirskUSSR

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