Mode transition and oscillation suppression in supersonic cavity flow

doi:10.1007/s10483-016-2095-9

Applied Mathematics and Mechanics (English Edition) ›› 2016, Vol. 37 ›› Issue (7): 941-956.doi: https://doi.org/10.1007/s10483-016-2095-9

Mode transition and oscillation suppression in supersonic cavity flow

Chao ZHANG, Zhenhua WAN, Dejun SUN

Department of Modern Mechanics, University of Science and Technology of China, Hefei 230027, China

收稿日期:2015-11-10 修回日期:2016-03-02 出版日期:2016-07-01 发布日期:2016-07-01
通讯作者: Dejun SUN E-mail:dsun@ustc.edu.cn
基金资助:
Project supported by the National Natural Science Foundation of China (Nos. 11232011 and 11402262), the 111 Project of China (No. B07033), the China Postdoctoral Science Foundation (No. 2014M561833), and the Fundamental Research Funds for the Central Universities

Mode transition and oscillation suppression in supersonic cavity flow

Chao ZHANG, Zhenhua WAN, Dejun SUN

Department of Modern Mechanics, University of Science and Technology of China, Hefei 230027, China

Received:2015-11-10 Revised:2016-03-02 Online:2016-07-01 Published:2016-07-01
Contact: Dejun SUN E-mail:dsun@ustc.edu.cn
Supported by:
Project supported by the National Natural Science Foundation of China (Nos. 11232011 and 11402262), the 111 Project of China (No. B07033), the China Postdoctoral Science Foundation (No. 2014M561833), and the Fundamental Research Funds for the Central Universities

摘要/Abstract

摘要：

Supersonic flows past two-dimensional cavities with/without control are investigated by the direct numerical simulation (DNS). For an uncontrolled cavity, as the thickness of the boundary layer declines, transition of the dominant mode from the steady mode to the Rossiter Ⅱ mode and then to the Rossiter Ⅲ mode is observed due to the change of vortex-corner interactions. Meanwhile, a low frequency mode appears. However, the wake mode observed in a subsonic cavity flow is absent in the current simulation. The oscillation frequencies obtained from a global dynamic mode decomposition (DMD) approach are consistent with the local power spectral density (PSD) analysis. The dominant mode transition is clearly shown by the dynamic modes obtained from the DMD. A passive control technique of substituting the cavity trailing edge with a quarter-circle is studied. As the effective cavity length increases, the dominant mode transition from the Rossiter Ⅱ mode to the Rossiter Ⅲ mode occurs. With the control, the pressure oscillations are reduced significantly. The interaction of the shear layer and the recirculation zone is greatly weakened, combined with weaker shear layer instability, responsible for the suppression of pressure oscillations. Moreover, active control using steady subsonic mass injection upstream of a cavity leading edge can stabilize the flow.

关键词: pressure oscillation, supersonic cavity flow, vortex-corner interaction, mode transition

Abstract:

Key words: supersonic cavity flow, pressure oscillation, vortex-corner interaction, mode transition

中图分类号:

Chao ZHANG, Zhenhua WAN, Dejun SUN. Mode transition and oscillation suppression in supersonic cavity flow[J]. Applied Mathematics and Mechanics (English Edition), 2016, 37(7): 941-956.

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Mode transition and oscillation suppression in supersonic cavity flow

Mode transition and oscillation suppression in supersonic cavity flow

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