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Transition of a Supersonic Boundary Layer Over an Unswept Wing Due to Acoustic Noise

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Abstract

In this paper, we present the results of direct numerical modeling of the process of susceptibility of a supersonic boundary layer over an unswept wing with a thin parabolic profile to acoustic noise of various intensities. It was demonstrated that acoustic noise can cause a laminar–turbulent transition over the unswept wing of a supersonic passenger aircraft.

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Funding

This work was support by the Russian Science Foundation, project no. 19-79-10132, using the computing resources of the federal Complex for Modeling and Processing Mega-class Data, Center for Collective Use, National Research Center, Kurchatov Institute, http://ckp.nrcki.ru/.

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Authors and Affiliations

  1. Zhukovskii Central Aerohydrodynamic Institute, 140181, Zhukovskii, Moscow oblast, Russia

    P. V. Chuvakhov &  I. V. Egorov

  2. Moscow Institute of Physics and Technology (National Research University), 141701, Dolgoprudnyi, Moscow oblast, Russia

    P. V. Chuvakhov &  I. V. Egorov

Authors
  1. P. V. Chuvakhov
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  2. I. V. Egorov
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Corresponding authors

Correspondence to P. V. Chuvakhov or I. V. Egorov.

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The authors declare that they have no conflicts of interest.

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Translated by A. Ivanov

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Chuvakhov, P.V., Egorov, I.V. Transition of a Supersonic Boundary Layer Over an Unswept Wing Due to Acoustic Noise. Dokl. Phys. 68, 131–134 (2023). https://doi.org/10.1134/S1028335823040031

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  • DOI: https://doi.org/10.1134/S1028335823040031

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