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3D versus 2D calculation of thrust characteristics of the air-breathing pulse detonation engine under supersonic flight conditions

  • Combustion, Explosion, and Shock Waves
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Russian Journal of Physical Chemistry B Aims and scope Submit manuscript

Abstract

3D calculations are used to confirm the conclusion that the specific thrust of the air-breathing pulse detonation engine is 20–30% higher than that of the ideal ramjet in which normal combustion takes place.

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References

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Authors and Affiliations

  1. National Research Nuclear University MEPhI, Kashirskoe sh. 31, Moscow, 115409, Russia

    A. E. Zangiev, V. S. Ivanov & S. M. Frolov

  2. Semenov Institute of Chemical Physics, Russian Academy of Sciences, ul. Kosygina 4, Moscow, 119991, Russia

    A. E. Zangiev, V. S. Ivanov & S. M. Frolov

  3. Pulse Detonation Combustion Center, ul. Kosygina 4, Moscow, 119991, Russia

    A. E. Zangiev, V. S. Ivanov & S. M. Frolov

Authors
  1. A. E. Zangiev
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  2. V. S. Ivanov
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  3. S. M. Frolov
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Corresponding author

Correspondence to S. M. Frolov.

Additional information

Original Russian Text © A.E. Zangiev, V.S. Ivanov, S.M. Frolov, 2014, published in Khimicheskaya Fizika, 2014, Vol. 33, No. 12, pp. 37–41.

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Zangiev, A.E., Ivanov, V.S. & Frolov, S.M. 3D versus 2D calculation of thrust characteristics of the air-breathing pulse detonation engine under supersonic flight conditions. Russ. J. Phys. Chem. B 8, 859–862 (2014). https://doi.org/10.1134/S1990793114110244

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  • DOI: https://doi.org/10.1134/S1990793114110244

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