Optimal growth and secondary instability of hypersonic blunt wedge boundary layers

ZHANG Haojie; LIU Jianxin; ZHAO Lei

doi:10.7638/kqdlxxb-2023.0193

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Optimal growth and secondary instability of hypersonic blunt wedge boundary layers

更新时间：2026-07-27

- Optimal growth and secondary instability of hypersonic blunt wedge boundary layers
- Vol. 42, Issue 8, Pages: 23-33(2024)
- 作者机构：
  
  1. 天津大学力学系,天津,300072
  2. 空天飞行空气动力科学与技术全国重点实验室,绵阳,621000
  3. 天津大学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-2023.0193
  CLC： O357.4+1;O354.4
- Published：2024
- 稿件说明：
移动端阅览
张浩杰, 刘建新, 赵磊. 高超声速钝楔边界层最优增长扰动及其二次失稳研究[J]. 空气动力学学报, 2024, 42(8): 23−33.

ZHANG Haojie, LIU Jianxin, ZHAO Lei. Optimal growth and secondary instability of hypersonic blunt wedge boundary layers[J]. 2024, 42(8): 23-33.
张浩杰, 刘建新, 赵磊. 高超声速钝楔边界层最优增长扰动及其二次失稳研究[J]. 空气动力学学报, 2024, 42(8): 23−33. DOI： 10.7638/kqdlxxb-2023.0193

ZHANG Haojie, LIU Jianxin, ZHAO Lei. Optimal growth and secondary instability of hypersonic blunt wedge boundary layers[J]. 2024, 42(8): 23-33. DOI： 10.7638/kqdlxxb-2023.0193.

摘要

最优增长扰动理论是近年来高超声速边界层非模态失稳现象研究中的主要理论之一，可被看作一种对非模态扰动增长的工程化估计。本文以高超声速钝楔边界层为研究对象，采用最优增长理论和二次失稳分析方法，对钝楔边界层的非模态失稳特性进行了研究。结果表明，在平楔面各个工况的有限计算域中无法找到不稳定模态扰动，非模态的最优增长扰动可获得较大的能量增益。研究还发现，最优扰动的能量增益随马赫数的增加逐渐减小，而壁面曲率对最优扰动的增长起促进作用。但是，由于不同曲率条件下对应的最大能量增长扰动的展向波数存在一定差异，因此变曲率的等熵压缩面不存在统一的变化规律。进一步，研究还采用非线性抛物化稳定性方程研究了零频率最优扰动的非线性演化，并以最优扰动形成的条纹边界层的二次稳定性为基本流，采用线性理论进行了二次失稳分析，发现最优增长扰动形成的条纹结构具有较强的二次失稳增长率，这有利于下游边界层转捩成湍流。该研究结果对设计高速飞行器前体进气道的强制转捩装置有一定参考意义。

Abstract

The optimal growth disturbance theory has been one of the main theories in recent years for studying non-modal instability phenomena in hypersonic boundary layers. This theory can be viewed as an engineering estimation of the growth of non-modal disturbances. The entire study focuses on hypersonic blunt wedge boundary layer

and employs the optimal growth disturbance theory and secondary instability analysis to investigate the non-modal instability characteristics of the blunt wedge boundary layer. The analysis reveals that no unstable modal disturbances can be found in the finite computational domains for various conditions on the flat wedge surface. However

non-modal optimal growth disturbances can acquire significant energy gains. The study also finds that the energy gain of the optimal disturbance gradually decreases with the increase in Mach number

while the wall curvature promotes the growth of the optimal disturbance. However

the spanwise wavenumber of disturbance with the maximum energy gain varies with the curvature condition

thus there is no uniform trend in curved isentropic compression surfaces. Furthermore

the study investigates the nonlinear evolution of the stationary optimal disturbance using the non-parallel parabolized stability equations and analyzes the secondary stability characteristics of the streaky boundary layer based on the linear stability theory. The results indicate that the streaky structure associated with the optimal growth has strong secondary instability

which is conducive to the transition of the downstream boundary layer to turbulence. These research findings have significant implications for the design of forced transition devices in the forebody inlets of hypersonic vehicles.

关键词

Keywords

references

MORKOVIN M V . Transition in open flow systems-a reassessment[J ] . Bull. am. phys. soc, 1994 , 39 : 1882 .

TREFETHEN L N, TREFETHEN A E, REDDY S C, et al . Hydrodynamic stability without eigenvalues[J ] . Science, 1993 , 261 ( 5121 ): 578 − 584 .

HANIFI A, SCHMID P J, HENNINGSON D S . Transient growth in compressible boundary layer flow[J ] . Physics of Fluids, 1996 , 8 ( 3 ): 826 − 837 .

ANDERSSON P, BERGGREN M, HENNINGSON D S . Optimal disturbances and bypass transition in boundary layers[J ] . Physics of Fluids, 1999 , 11 ( 1 ): 134 − 150 .

TUMIN A, RESHOTKO E . Spatial theory of optimal disturbances in boundary layers[J ] . Physics of Fluids, 2001 , 13 ( 7 ): 2097 − 2104 .

TUMIN A, RESHOTKO E . Optimal disturbances in compressible boundary layers[J ] . AIAA Journal, 2003 , 41 ( 12 ): 2357 − 2363 .

PRALITS J O, BYSTRÖM M G, HANIFI A, et al . Optimal disturbances in three-dimensional boundary-layer flows[J ] . ERCOFTAC Bulletin, 2007 , 74 : 23 − 31 .

REN J, FU S, HANIFI A . Stabilization of the hypersonic boundary layer by finite-amplitude streaks[J ] . Physics of Fluids, 2016 , 28 ( 2 ): 024110 .

Berry S A , Difulvio M , Kowalkowski M K. Forced boundary-layer transition on X-43 (hyper-X) in NASA LaRC 20-inch Mach 6 air tunnel[J]. Post-Print, 2000, 15(2): 329−330.

BERRY S, DARYABEIGI K, WURSTER K, et al . Boundary layer transition on X-43A[J ] . Journal of Spacecraft Rockets, 2014 , 47 ( 6 ): 922 − 934 .

Mathew P B. Laminar instability and transition on the X-51 [D]. Purdue University, 2009.

KIMMEL R, ADAMCZAK D W, GOSSE R, et al. Ground test and computation of boundary layer transition on the hypersonic international flight research and experimentation (HIFiRE)-5 vehicle[R]. Air Force Research Lab Wright-patterson Afb Oh Air Vehicles Directorate, 2011.

ZHAO H Y, ZHOU Y, NI H L, et al . Test of forced boundary-layer transiti on on hypersonic inlet[J ] . Journal of Experiments in Fluid Mechanics, 2012 , 26 ( 1 ): 1 − 6 (in Chinese).

TU G H, YAN Z G, ZHAO X H, et al . SA and SST turbulence models for hypersonic forced boundary layer transition[J ] . Acta Aeronautica et Astronautica Sinica, 2015 , 36 ( 5 ): 1471 − 1479 (in Chinese).

ZHANG H J, SHEN Q . A new method of artificial boundary layer transition for hypersonic inlet[J ] . Journal of Experiments in Fluid Mechanics, 2016 , 30 ( 2 ): 75 − 78,102 (in Chinese).

ZHANG H J, ZHU Z B, SHANG Q, et al . Large eddy simulation of hypersonic inlet boundary layer transition triggered by zig-zag trip[J ] . Acta Aeronauticaet Astronautica Sinica, 2019 , 40 ( 10 ): 122930 (in Chinese).

RESHOTKO E, TUMIN A. The blunt body paradox—a case for transient growth[M]// Laminar-Turbulent Transition. Berlin, Heidelberg: Springer Berlin Heidelberg, 2000: 403−3408.

PAREDES P, CHOUDHARI M M, LI F . Blunt-body paradox and transient growth on a hypersonic spherical forebody[J ] . Physical Review Fluids, 2017 , 2 ( 5 ): 053903 .

ZHANG Y M. Applications of PSE to evolution of disturbances in compressible boundary layers and to secondary instability in supersonic boundary layers[D]. Tianjin: Tianjin University, 2008 (in Chinese).

WANG Y T, LIU J X, WANG X K, et al . Effects of porous wall on secondary instability of optimal growth streaks in high speed boundary layers[J ] . Acta Aeronautica et Astronautica Sinica, 2023 , 44 ( 22 ): 128519 (in Chinese).

LI X L, FU D X, MA Y W . Direct numerical simulation of hypersonic boundary layer transition over a blunt cone[J ] . AIAA Journal, 2008 , 46 ( 11 ): 2899 − 2913 .

WAN B B. Study on sensitivity of hypersonic blunt body boundary layer considering entropy layer[D]. Tianjin: Tianjin University, 2018 (in Chinese).

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Numerical study on cross-flow transition in three-dimensional hypersonic boundary layers

Effect of key parameters on receptivity of high-speed cone boundary layer to freestream slow acoustic waves

Numerical simulation of the effect of transition position on static and dynamic aerodynamic characteristics of cones

Evolution and development of flow transition and supersonic modes under high-temperature gas effects

Numerical research progress and prediction software of transition in hypersonic three-dimensional boundary layer

Related Author

MA Shaoxian

SU Caihong

HAN Yufeng

Chen Jianqiang

Tu Guohua

WAN Bingbing

Li Chenhui

Chen Yining

Related Institution

The Laboratory of High Speed Aerodynamics, School of Mechanical Engineering, Tianjin University

School of Aeronautic Science and Engineering, Beihang University , Beijing

China Aerodynamics Research and Development Center, Mianyang

School of Aerospace Engineering, Tsinghua University, Beijing

School of Mechanical Engineering, Tianjin University, Tianjin

AI问答

⁰