Numerical study of the suction flow control of the supersonic boundary layer transition in a framework of gas-kinetic scheme

Di Sun; Feng Qu; Chaoyu Liu; Fangzhou Yao; Junqiang Bai

doi:10.1016/j.ast.2020.106397

Numerical study of the suction flow control of the supersonic boundary layer transition in a framework of gas-kinetic scheme

Di Sun, Feng Qu, Chaoyu Liu, Fangzhou Yao, Junqiang Bai

School of Aeronautics

Northwestern Polytechnical University Xian

Research output: Contribution to journal › Article › peer-review

8 Scopus citations

Abstract

In this paper, we numerically study the supersonic boundary layer transition process and the suction flow control method by employing the DNS technology. By adopting the high resolution GKS method, the mechanism of the boundary transition and the statistical characteristics of the compressible turbulent boundary layer are investigated. Results indicate that the streamwise vortex and the three-dimensional shear layer with high instability are the main causes of the boundary layer transition. Suction control cases show that the laminar boundary layer suction can weaken the development of the unstable disturbance waves in the boundary layer, and delay the streamwise position of the local disturbance. Also, the space distributions of the vortex structure are weakened to delay the process of the transition.

Original language	English
Article number	106397
Journal	Aerospace Science and Technology
Volume	109
DOIs	https://doi.org/10.1016/j.ast.2020.106397
State	Published - Feb 2021

Keywords

Computational fluid dynamics
Direct numerical simulation
Gas-kinetic scheme
Supersonic boundary transition

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title = "Numerical study of the suction flow control of the supersonic boundary layer transition in a framework of gas-kinetic scheme",

abstract = "In this paper, we numerically study the supersonic boundary layer transition process and the suction flow control method by employing the DNS technology. By adopting the high resolution GKS method, the mechanism of the boundary transition and the statistical characteristics of the compressible turbulent boundary layer are investigated. Results indicate that the streamwise vortex and the three-dimensional shear layer with high instability are the main causes of the boundary layer transition. Suction control cases show that the laminar boundary layer suction can weaken the development of the unstable disturbance waves in the boundary layer, and delay the streamwise position of the local disturbance. Also, the space distributions of the vortex structure are weakened to delay the process of the transition.",

keywords = "Computational fluid dynamics, Direct numerical simulation, Gas-kinetic scheme, Supersonic boundary transition",

author = "Di Sun and Feng Qu and Chaoyu Liu and Fangzhou Yao and Junqiang Bai",

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T1 - Numerical study of the suction flow control of the supersonic boundary layer transition in a framework of gas-kinetic scheme

AU - Sun, Di

AU - Qu, Feng

AU - Liu, Chaoyu

AU - Yao, Fangzhou

AU - Bai, Junqiang

PY - 2021/2

Y1 - 2021/2

N2 - In this paper, we numerically study the supersonic boundary layer transition process and the suction flow control method by employing the DNS technology. By adopting the high resolution GKS method, the mechanism of the boundary transition and the statistical characteristics of the compressible turbulent boundary layer are investigated. Results indicate that the streamwise vortex and the three-dimensional shear layer with high instability are the main causes of the boundary layer transition. Suction control cases show that the laminar boundary layer suction can weaken the development of the unstable disturbance waves in the boundary layer, and delay the streamwise position of the local disturbance. Also, the space distributions of the vortex structure are weakened to delay the process of the transition.

AB - In this paper, we numerically study the supersonic boundary layer transition process and the suction flow control method by employing the DNS technology. By adopting the high resolution GKS method, the mechanism of the boundary transition and the statistical characteristics of the compressible turbulent boundary layer are investigated. Results indicate that the streamwise vortex and the three-dimensional shear layer with high instability are the main causes of the boundary layer transition. Suction control cases show that the laminar boundary layer suction can weaken the development of the unstable disturbance waves in the boundary layer, and delay the streamwise position of the local disturbance. Also, the space distributions of the vortex structure are weakened to delay the process of the transition.

KW - Computational fluid dynamics

KW - Direct numerical simulation

KW - Gas-kinetic scheme

KW - Supersonic boundary transition

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DO - 10.1016/j.ast.2020.106397

M3 - 文章

AN - SCOPUS:85098462465

SN - 1270-9638

VL - 109

JO - Aerospace Science and Technology

JF - Aerospace Science and Technology

M1 - 106397

ER -

Numerical study of the suction flow control of the supersonic boundary layer transition in a framework of gas-kinetic scheme

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