Stability of fundamental secondary instability streaky structures in a hypersonic boundary layer

LI Lingyu; LIU Jianxin

doi:10.7638/kqdlxxb-2020.0122

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Stability of fundamental secondary instability streaky structures in a hypersonic boundary layer

更新时间：2026-05-28

- Stability of fundamental secondary instability streaky structures in a hypersonic boundary layer
- Vol. 39, Issue 5, Pages: 63-74(2021)
- 作者机构：
  
  天津大学机械工程学院高速空气动力学研究室,天津,300072
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2020.0122
  CLC： O317
- Published：2021
- 稿件说明：
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李玲玉, 刘建新. 高超声速边界层基频二次失稳条纹结构的稳定性[J]. 空气动力学学报, 2021, 39(5): 63−74.

LI Lingyu, LIU Jianxin. Stability of fundamental secondary instability streaky structures in a hypersonic boundary layer[J]. 2021, 39(5): 63-74.
李玲玉, 刘建新. 高超声速边界层基频二次失稳条纹结构的稳定性[J]. 空气动力学学报, 2021, 39(5): 63−74. DOI： 10.7638/kqdlxxb-2020.0122

LI Lingyu, LIU Jianxin. Stability of fundamental secondary instability streaky structures in a hypersonic boundary layer[J]. 2021, 39(5): 63-74. DOI： 10.7638/kqdlxxb-2020.0122.

摘要

近年来在高超声速边界层的直接数值模拟和静风洞实验研究中，相继发现了边界层转捩前出现的典型基频模态二次失稳现象，其主要成分为流向条纹结构。全文以高超声速平板边界层为研究对象，采用线性稳定性分析和二次稳定性分析的方法，对边界层内条纹结构的产生机制和无黏稳定性特征进行了研究。结果表明：首次失稳扰动幅值对二次失稳类型有影响。当首次失稳扰动幅值较大时，基频模态占主导，其主要成分为条纹结构，表现为流向涡。该条纹结构存在着多个无黏失稳模态，其中低频模态对应于第一模态在三维边界层内的扩展，高频模态对应于可压缩的第二模态。这一研究成果为进一步开展高超声速边界层转捩机制研究奠定了基础。

Abstract

The fundamental secondary instability mode can be observed in the earlier stage of hypersonic boundary layer transition in recent direct numerical simulations and quiet wind tunnel experiments

which suggest the existence of streamwise streaks. This study investigated the generation mechanism of these streaky structures and their inviscid instability. In order to simplify the problem

the hypersonic boundary layer over a flat plate was focused on

and the instability was analyzed using both the linear stability theory (LST) and the secondary instability analysis (SIA). The results suggest that the dominant secondary instability mode can be affected by the amplitude of the two-dimensional primary mode (the second mode). When its amplitude is large

the fundamental mode is the dominant one

and mainly consists of streamwise streaky structures

or streamwise vortices. Inviscid bi-global analysis was used to investigate the instability of the streaks

and multiple inviscid modes were identified. The modes with lower frequencies can be seen as the extension of the first mode

and those with higher frequencies correspond to the second mode induced by the compressibility. This work makes a contribution on understanding the mechanism of hypersonic boundary layer breakdown.

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references

LUO J S. Transition and prediction for hypersonic boundary layers[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1): 357-372(in Chinese).

LIU J X. A numerical investigation on inviscid instability of streaky structures in incompressible boundary layer flow[D]. Tianjin: Tianjin University, 2007 (in Chinese).

ZHANG C B. Research on nonlinear mode interactions relating to supersonic boundary layer transition[D]. Tianjin: Tianjin University, 2017(in Chinese).

KLEBANOFF P S, TIDSTROM K D, SARGENT L M. The three-dimensional nature of boundary-layer transition[J]. Journal of Fluid Mechanics, 1962, 12(01): 1-34.DOI: 10.1017/S0022112062000014.

KACHANOV Y S, YA LEVCHENKO V. The resonant interaction of disturbances at laminar-turbulent transition in a boundary layer[J]. Journal of Fluid Mechanics, 1984, 138: 209-247.

HERBERT T. Analysis of the subharmonic route to transition in boundary layers[C ] //22nd Aerospace Sciences Meeting, Reno, NV. Reston, Virginia: AIAA, 1984. doi: 10.2514/6.1984-9

HERBERT T. Secondary instability of boundary layers[J]. Annual Review of Fluid Mechanics, 1988, 20(1): 487-526.DOI: 10.1146/annurev.fl.20.010188.002415.

NG L L, ERLEBACHER G. Secondary instabilities in compressible boundary layers[J]. Physics of Fluids A: Fluid Dynamics, 1992, 4(4): 710-726.DOI: 10.1063/1.858290.

LIU J X. Evolution of disturbance in hypersonic blunt cone boundary layer at small angle of attack[D]. Tianjin: Tianjin University, 2010 (in Chinese).

CHOU A, WARD C, LETTERMAN L, et al. Transition research with temperature-sensitive paints in the boeing/AFOSR Mach-6 quiet tunnel[C ] //41st AIAA Fluid Dynamics Conference and Exhibit, Honolulu, Hawaii. Reston, Virginia: AIAA, 2011. doi: 10.2514/6.2011-3872

YU M, LUO J S. Nonlinear interaction mechanisms of disturbances in supersonic flat-plate boundary layers[J]. Science China Physics, Mechanics Astronomy, 2014, 57(11): 2141-2151.DOI: 10.1007/s11433-014-5568-0.

SIVASUBRAMANIAN J, FASEL H F. Direct numerical simulation of laminar-turbulent transition in a flared cone boundary layer at Mach 6[C ] //54th AIAA Aerospace Sciences Meeting, San Diego, California, USA. Reston, Virginia: AIAA, 2016. doi: 10.2514/6.2016-0846

HADER C, LEINEMANN M, FASEL H F. Direct numerical simulations of hypersonic boundary-layer transition for a flared cone: fundamental breakdown[J]. Journal of Fluid Mechanics, 2019, 869: 341-384. https://doi.org/10.1017/jfm.2019.202

LIU J X. The fundamental secondary instability of the primary mack mode in hypersonic boundary layers on flat plates[J]. Advances in Applied Mathematics and Mechanics, 2019, 11(3): 559-570.DOI: 10.4208/aamm.2018.s01.

YU G T. Application of e-N method and prediction of disturbances propagation in three-dimensional hypersonic boundary layers[D]. Tianjin: Tianjin University, 2016 (in Chinese).

WARD C, HENDERSON R, SCHNEIDER S P. Secondary instability of stationary crossflow vortices on an inclined cone at Mach 6[C ] //45th AIAA Fluid Dynamics Conference, Dallas, TX. Reston, Virginia: AIAA, 2015. doi: 10.2514/6.2015-2773

LI F, CHOUDHARI M, CHANG C L, et al. Development and breakdown of Görtler vortices in high speed boundary layers[C ] //48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Orlando, Florida. Reston, Virginia: AIAA, 2010. doi: 10.2514/6.2010-705

PAREDES P, THEOFILIS V. Centerline instabilities on the hypersonic international flight research experimentation HIFiRE-5 elliptic cone model[J]. Journal of Fluids and Structures, 2015, 53: 36-49.DOI: 10.1016/j.jfluidstructs.2014.11.002.

REN J. Secondary instabilities of Görtler vortices in high-speed boundary layers and control on flow transition[D]. Beijing: Tsinghua University, 2015 (in Chinese).

LEIB S J, WUNDROW D W, GOLDSTEIN M E. Effect of free-stream turbulence and other vortical disturbances on a laminar boundary layer[J]. Journal of Fluid Mechanics, 1999, 380: 169-203.

ZHOU H, SU C H, ZHANG Y M. Transition mechanism and prediction of supersonic/high supersonic boundary layer[M]. Beijing: Science Press, 2015 (in Chinese).

LEHOUCQ R B, SORENSEN D C, YANG C. ARPACK users' guide: solution of large-scale eigenvalue problems with implicitly restarted Arnoldi methods[M]. DBLP, 1998.

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