Mach Wave Effect on Laminar-Turbulent Transition in Supersonic Flow over a Flat Plate

被引：18

作者：

Din, Q. H. ^{[1
]}

Egorov, I. V. ^{[1
,2
]}

Fedorov, A. V. ^{[1
]}

机构：

[1] Moscow Inst Sci & Technol, Inst Per 9, Dolgoprudnyi 141701, Moscow Oblast, Russia

[2] Cent Aerohydrodynam Inst TsAGI, Ul Zhukovskogo 1, Zhukovskii 140180, Moscow Oblast, Russia

来源：

FLUID DYNAMICS | 2018年 / 53卷 / 05期

基金：

俄罗斯基础研究基金会;

关键词：

numerical modeling; quasistationary wake; Mach waves; Tollmien-Schlichting waves; supersonic flow; boundary layer;

D O I：

10.1134/S0015462818050063

中图分类号：

O3 [力学];

学科分类号：

08 ; 0801 ;

摘要：

The effect of a Mach wave (N wave) on laminar-turbulent transition induced by the first instability mode (Tollmien-Schlichting wave) in the flat-plate boundary layer is investigated on the basis of the numerical solution of Navier-Stokes equations at the freestream Mach number of 2.5. In accordance with the experiment, the N wave is generated by a two-dimensional roughness at the computation domain boundary corresponding to the side wall of the test section of a wind tunnel. It is shown that the disturbance induced by the backward front of the N wave in the boundary layer has no effect on the beginning of transition but displaces downstream the nonlinear stage of the first mode development. The disturbance induced by the forward front of the N wave displaces the beginning of transition upstream.

引用

页码：690 / 701

页数：12

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