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Numerical Modeling in Conjugate Formulation of the Temperature State of the Leading Edge of Hypersonic Flying Vehicles under Different Methods of Organization of the Cooling System

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Abstract

Heat transfer in the region of the leading edge of a hypersonic flying vehicle has been calculated by finite‐difference integration of the Reynolds equations closed by the low‐Reynolds version of the k–ε model of turbulence. Integration has been performed using the explicit–implicit McCormack scheme. It is shown that blowing of a cooling agent through a porous insert can lead to a substantial decrease of heat flux. The Darcy equation was used in solution of the conjugate problem.

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REFERENCES

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Authors and Affiliations

  1. Academy of Civil Aviation, 38 Pilotov Street, St. Petersburg, 169210, Russia

    S. A. Isaev & G. S. Sadovnikov

  2. N. É. Bauman Moscow Technical University, Russia

    A. I. Leont'ev & V. V. Nosatov

Authors
  1. S. A. Isaev
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  2. A. I. Leont'ev
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  3. G. S. Sadovnikov
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  4. V. V. Nosatov
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Isaev, S.A., Leont'ev, A.I., Sadovnikov, G.S. et al. Numerical Modeling in Conjugate Formulation of the Temperature State of the Leading Edge of Hypersonic Flying Vehicles under Different Methods of Organization of the Cooling System. Journal of Engineering Physics and Thermophysics 76, 1043–1047 (2003). https://doi.org/10.1023/B:JOEP.0000003218.82078.c9

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  • DOI: https://doi.org/10.1023/B:JOEP.0000003218.82078.c9

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