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Computation of hypersonic flow and radiation of viscous chemically reacting gas in a channel modeling a section of a scramjet

  • Heat and Mass Transfer and Physical Gasdynamics
  • Published:
High Temperature Aims and scope

Abstract

This work is devoted to a consideration of flow and combustion of a hydrogen-air mixture in a channel modeling a section of a supersonic combustion ramjet (scramjet). Fields of concentrations, pressure, and temperature are obtained. Based on them, the thermal radiation of gas within a scramjet combustor is computed. The density of the radiative heat flux to the chamber wall is computed by two methods, i.e., in a P1 approximation of the spherical harmonics method and in an approximation of the plane layer. It has been shown that the radiative heat flux contribute significantly to the total heating of the jet wall.

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Authors and Affiliations

  1. Ishlinskii Institute for Problems of Mechanics, Russian Academy of Sciences, pr. Vernadskogo 101, Moscow, 117526, Russia

    D. V. Kotov & S. T. Surzhikov

Authors
  1. D. V. Kotov
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  2. S. T. Surzhikov
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Additional information

Original Russian Text © D.V. Kotov, S.T. Surzhikov, 2012, published in Teplofizika Vysokikh Temperatur, 2012, Vol. 50, No. 1, pp. 126–136.

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Kotov, D.V., Surzhikov, S.T. Computation of hypersonic flow and radiation of viscous chemically reacting gas in a channel modeling a section of a scramjet. High Temp 50, 120–130 (2012). https://doi.org/10.1134/S0018151X12010099

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  • DOI: https://doi.org/10.1134/S0018151X12010099

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