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Heating of Two-Layer Thermal Protection Coating at Hypersonic Flow around a Spherical Blunting

  • AIRCRAFT AND ROCKET ENGINE THEORY
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Abstract

The nonstationary problem of thermal conductivity in a two-layer thermal protection coating is under consideration. The solution is given for a metal hemispherical shell with axisymmetrical distribution of the heat flux density over the outer surface of the coating.

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ACKNOWLEDGEMENTS

This work was supported by the Russian Foundation for Basic Research, project no. 18-38-20108.

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Authors and Affiliations

  1. Bauman Moscow State Technical University, ul. 2ya Baumanskaya 5, 105005, Moscow, Russia

    V. S. Zarubin, V. N. Zimin, V. V. Leonov & V. S. Zarubin Jr.

Authors
  1. V. S. Zarubin
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  2. V. N. Zimin
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  3. V. V. Leonov
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  4. V. S. Zarubin Jr.
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Corresponding author

Correspondence to V. V. Leonov.

Additional information

Translated from Izvestiya Vysshikh Uchebnykh Zavedenii, Aviatsionnaya Tekhnika, 2021, No. 1, pp. 81 - 89.

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Zarubin, V.S., Zimin, V.N., Leonov, V.V. et al. Heating of Two-Layer Thermal Protection Coating at Hypersonic Flow around a Spherical Blunting. Russ. Aeronaut. 64, 87–96 (2021). https://doi.org/10.3103/S1068799821010116

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  • DOI: https://doi.org/10.3103/S1068799821010116

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