Transition control of Mach 6.5 hypersonic flat plate boundary layer

doi:10.1007/s10483-019-2423-8

Applied Mathematics and Mechanics (English Edition) ›› 2019, Vol. 40 ›› Issue (2): 283-292.doi: https://doi.org/10.1007/s10483-019-2423-8

Transition control of Mach 6.5 hypersonic flat plate boundary layer

Yunchi ZHANG^1,2, Chi LI^1,2

1. State Key Laboratory for Turbulence and Complex Systems, Peking University, Beijing 100871, China;
2. Department of Aeronautics and Astronautics, College of Engineering, Peking University, Beijing 100871, China

收稿日期:2018-09-05 修回日期:2018-10-15 出版日期:2019-02-01 发布日期:2019-02-01
通讯作者: Yunchi ZHANG E-mail:zhangyunchi@pku.edu.cn
基金资助:
Project supported by the National Natural Science Foundation of China (Nos. 10921202, 11221061, 11632002, 11521091, 91752000, and 11602005)

Transition control of Mach 6.5 hypersonic flat plate boundary layer

Yunchi ZHANG^1,2, Chi LI^1,2

1. State Key Laboratory for Turbulence and Complex Systems, Peking University, Beijing 100871, China;
2. Department of Aeronautics and Astronautics, College of Engineering, Peking University, Beijing 100871, China

Received:2018-09-05 Revised:2018-10-15 Online:2019-02-01 Published:2019-02-01
Contact: Yunchi ZHANG E-mail:zhangyunchi@pku.edu.cn
Supported by:
Project supported by the National Natural Science Foundation of China (Nos. 10921202, 11221061, 11632002, 11521091, 91752000, and 11602005)

摘要/Abstract

摘要： An artificial disturbance is introduced into the boundary layer over a flat plate to investigate the effect on the transition process in the Mach 6.5 wind tunnel at Peking University. A linear stability theory (LST) is utilized to predict the evolution of the eigenmodes, and the frequency of the artificial disturbance is chosen according to the LST results. The artificial disturbance is generated by glowing discharge on the surface of the plate close to the leading edge. The Rayleigh-scattering visualization and particle image velocimetry (PIV) measurements are performed. By comparing the experimental results with artificial disturbances with those under the natural condition (without artificial disturbances), the present paper shows that the second-mode instability waves are significantly stimulated by the artificial disturbances, and the boundary layer transition is effectively triggered.

关键词: turbulent eddies, turbulent eddy interaction, transition control, glowing discharge, creation and annihilation of turbulent eddies, hypersonic, boundary layer

Abstract: An artificial disturbance is introduced into the boundary layer over a flat plate to investigate the effect on the transition process in the Mach 6.5 wind tunnel at Peking University. A linear stability theory (LST) is utilized to predict the evolution of the eigenmodes, and the frequency of the artificial disturbance is chosen according to the LST results. The artificial disturbance is generated by glowing discharge on the surface of the plate close to the leading edge. The Rayleigh-scattering visualization and particle image velocimetry (PIV) measurements are performed. By comparing the experimental results with artificial disturbances with those under the natural condition (without artificial disturbances), the present paper shows that the second-mode instability waves are significantly stimulated by the artificial disturbances, and the boundary layer transition is effectively triggered.

Key words: turbulent eddies, creation and annihilation of turbulent eddies, turbulent eddy interaction, hypersonic, boundary layer, transition control, glowing discharge

中图分类号:

76K05

Yunchi ZHANG, Chi LI. Transition control of Mach 6.5 hypersonic flat plate boundary layer[J]. Applied Mathematics and Mechanics (English Edition), 2019, 40(2): 283-292.

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Transition control of Mach 6.5 hypersonic flat plate boundary layer

Transition control of Mach 6.5 hypersonic flat plate boundary layer

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