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To the Theory of Hypersonic Flow around a Thin Delta Finite-Swept Wing at a Large Attack Angle

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Abstract

The paper reviews the most important results in solving the problem of a hypersonic flow around a thin finite-swept delta wing at large angles of attack close to the right angle obtained by the author using the thin shock-layer method. The classification of all the basic modes and schemes of the flows realized in the proposed theory is supplemented by the two main similarity parameters. A composite solution, which adequately represents the disturbed flow both in the main shock-layer part and in the near-wall entropy layer, is obtained.

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Authors and Affiliations

  1. Zhukovsky Central Aerohydrodynamic Institute, 140181, Zhukovsky, Moscow Region, Russia

    V. N. Golubkin

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  1. V. N. Golubkin
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Correspondence to V. N. Golubkin.

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Translated by E. Oborin

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Golubkin, V.N. To the Theory of Hypersonic Flow around a Thin Delta Finite-Swept Wing at a Large Attack Angle. Fluid Dyn 55, 904–914 (2020). https://doi.org/10.1134/S0015462820070058

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  • DOI: https://doi.org/10.1134/S0015462820070058

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