Response of the Shock Wave/Boundary Layer Interaction to Disturbances Induced by the Plasma Discharge

被引：1

作者：

Vishnyakov, Oleg ^{[1
]}

Polivanov, Pavel ^{[1
]}

Sidorenko, Andrey ^{[1
]}

机构：

[1] Khristianovich Inst Theoret & Appl Mech SB RAS, Inst Skaya 4-1, Novosibirsk 630090, Russia

来源：

AEROSPACE | 2023年 / 10卷 / 09期

关键词：

flow control; DBD; plasma actuators; supersonic flow; SWBLI; LOW-FREQUENCY UNSTEADINESS; LAMINAR-TURBULENT TRANSITION; PARTICLE IMAGE VELOCIMETRY; BOUNDARY-LAYER; INDUCED SEPARATION; WAVE; FLOW; RECEPTIVITY; SIMULATION; BUFFET;

D O I：

10.3390/aerospace10090798

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The paper focuses on the investigation of unsteady effects in shock wave/boundary layer interaction. The study was carried out using a flat plate model subjected to a free stream Mach number of 1.43 and a unit Reynolds number (Re1) of 11.5 x 106 1/m. To generate two-dimensional disturbances in the laminar boundary layer upstream of the separation region, a dielectric barrier discharge was employed. The disturbances were generated within the frequency range of 500 to 1700 Hz. The Strouhal numbers based on the length of the separation bubble ranged from 0.04 to 0.13. The measurements were carried out using a hot-wire anemometer. Analysis of the data shows that disturbances in this frequency range mostly decay. The maximum amplitudes of perturbations were observed at frequencies of 1250 Hz and 1700 Hz.

引用

页数：24

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