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Shock-wave flow regimes at entry into the diffuser of a hypersonic ramjet engine: Influence of physical properties of the gas medium

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Abstract

The physical aspects of the effective-adiabatic-exponent model making it possible to decompose the total problem on modeling of high-velocity gas flows into individual subproblems (“physicochemical processes” and “ aeromechanics”), which ensures the creation of a universal and efficient computer complex divided into a number of independent units, have been analyzed. Shock-wave structures appearing at entry into the duct of a hypersonic aircraft have been investigated based on this methodology, and the influence of the physical properties of the gas medium in a wide range of variations of the effective adiabatic exponent has been studied.

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Authors and Affiliations

  1. Institute of Computational Mathematics and Mathematical Geophysics, Siberian Branch of the Russian Academy of Sciences, 6 Akad. Lavrent’ev Ave., Novosibirsk, 630090, Russia

    G. A. Tarnavskii

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  1. G. A. Tarnavskii
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__________

Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 79, No. 4, pp. 69–80, July–August, 2006.

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Tarnavskii, G.A. Shock-wave flow regimes at entry into the diffuser of a hypersonic ramjet engine: Influence of physical properties of the gas medium. J Eng Phys Thermophys 79, 699–711 (2006). https://doi.org/10.1007/s10891-006-0155-5

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  • DOI: https://doi.org/10.1007/s10891-006-0155-5

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