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

IF 0.6 4区物理与天体物理 Q4 MECHANICS

Doklady Physics Pub Date : 2023-12-26 DOI:10.1134/S1028335823040031

P. V. Chuvakhov, I. V. Egorov

引用次数: 0

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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声学噪声导致未下垂机翼上超音速边界层的转变

摘要在本文中，我们介绍了对具有薄抛物线轮廓的非后掠翼上的超音速边界层易受不同强度声学噪声影响的过程进行直接数值建模的结果。结果表明，声学噪声可导致超音速客机无后掠面机翼上的层流-湍流过渡。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

Doklady Physics 物理-力学

CiteScore

1.40

自引率

12.50%

发文量

审稿时长

4-8 weeks

期刊介绍： Doklady Physics is a journal that publishes new research in physics of great significance. Initially the journal was a forum of the Russian Academy of Science and published only best contributions from Russia in the form of short articles. Now the journal welcomes submissions from any country in the English or Russian language. Every manuscript must be recommended by Russian or foreign members of the Russian Academy of Sciences.