凹腔对高超声速边界层稳定性的影响

冯烁; 王伯福; 涂国华; 武健辉; 陈坚强; 杨强

doi:10.7638/kqdlxxb-2022.0169

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凹腔对高超声速边界层稳定性的影响

研究论文 | 更新时间：2026-05-28

- 凹腔对高超声速边界层稳定性的影响
- Influence of cavities on hypersonic boundary layer transition
- 空气动力学学报 2023年41卷第11期页码：56-70
- 作者机构：
  
  1. 上海大学力学与工程科学学院，上海市应用数学和力学研究所,上海,200072
  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. 中国运载火箭技术研究院,北京,100076
- 作者简介：
  
  冯烁（1998—），男，安徽亳州人，硕士研究生，研究方向：流动稳定性. E-mail：ifshuo@outlook.com
  王伯福*，教授，研究方向：湍流与流动稳定性. E-mail：bofuwang@shu.edu.cn
  杨强*，助理研究员，研究方向：高超声速边界层转捩. E-mail：qiang.yang@skla.cardc.cn
- 基金信息：
  
  国家自然科学基金（92052301，12272395，11972220），空天飞行空气动力科学与技术全国重点实验室开放课题
- DOI：10.7638/kqdlxxb-2022.0169
  中图分类号： O357.4+1
- 纸质出版：2023
- 稿件说明：
移动端阅览
冯烁, 王伯福, 涂国华, 等. 凹腔对高超声速边界层稳定性的影响[J]. 空气动力学学报, 2023, 41(11): 56−70.

FENG Shuo, WANG Bofu, TU Guohua, et al. Influence of cavities on hypersonic boundary layer transition[J]. 2023, 41(11): 56-70.
冯烁, 王伯福, 涂国华, 等. 凹腔对高超声速边界层稳定性的影响[J]. 空气动力学学报, 2023, 41(11): 56−70. DOI： 10.7638/kqdlxxb-2022.0169

FENG Shuo, WANG Bofu, TU Guohua, et al. Influence of cavities on hypersonic boundary layer transition[J]. 2023, 41(11): 56-70. DOI： 10.7638/kqdlxxb-2022.0169.

摘要

凹腔广泛存在于航空航天飞行器表面，如部件安装缝隙、高温烧蚀剥离等，对边界层转捩过程具有重要影响，是飞行器气动设计需要重点考虑的因素之一。为了探究不同尺度凹腔对边界层扰动波的影响规律，本文在固定来流条件下针对不同尺度的壁面凹腔，采用线性稳定性分析和高精度直接数值模拟，研究了高超声速（

= 5.92）和超声速（

= 1.38）边界层内扰动波经过凹腔的演化过程。结果表明：凹腔内部存在较强的回流区，其涡结构随着凹腔尺寸的增大变得复杂。对于高超声速流动，当凹腔位于快慢模态同步点上游时会促进扰动波发展，而位于同步点附近或下游时则起到抑制作用，且当凹腔位于同步点位置时抑制效果最佳；增加凹腔尺度（宽度或深度）会强化其对扰动波的控制效果。对于超声速流动，在不稳定区间范围内凹腔总是促进扰动波增长，并且随着凹腔尺度的增加促进效果增强。当凹腔尺度超过临界值后，凹腔内流动会发生自激振荡，进而给下游边界层引入新的扰动源，促进转捩的发生。本文研究结果对飞行器表面气动设计与热防护提供了重要参考。

Abstract

Cavities such as installation gaps and high-temperature ablation stripping widely exist on the surfaces of aerospace vehicles. Their effects on the boundary-layer transition process are vital and thus need to be considered in the aircraft aerodynamic design. In order to explore the influence of cavities on the boundary-layer transition

this paper studies the evolutions of disturbance waves in both hypersonic (

= 5.92) and supersonic (

= 1.38) boundary layers passing through cavities of different sizes by using linear stability analysis and high-precision direct

numerical simulations. The results show a strong recirculation zone inside the cavity

in which vortical structures become more complex with the increase of the cavity size. For hypersonic flows

when the cavity is located upstream of the synchronization points of the fast and slow modes

it promotes the development of disturbance waves. However

the opposite is true when the cavity is located near or downstream of the synchronization points. The suppression effect is the most significant for the cavity located at the synchronization point. Increasing the cavity size (width or depth) will strengthen its control effect on disturbance waves. For supersonic flows

the cavity always promotes disturbance growth in unstable regions

and the promotion effect increases with the increase of the cavity size. When the cavity size exceeds the critical value

the flow in the cavity can generate self-excited oscillations

which will introduce new disturbance sources to the downstream boundary layers and promote the transition. The results of this study are essential for aerodynamic design and thermal protection of aircraft surfaces.

关键词

Keywords

references

CHEN J Q, TU G H, ZHANG Y F, et al. Hypersnonic boundary layer transition: what we know, where shall we go[J]. Acta Aerodynamica Sinica, 2017, 35(3): 311-337 (in Chinese).

EVERHART J L, ALTER S J, MERSKI N R, et al. Pressure gradient effects on hypersonic cavity flow heating[C]// 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virigina: AIAA, 2006: 185. doi: 10.2514/6.2006-185

MORGENSTERN A Jr, CHOKANI N. Hypersonic flow past open cavities[J]. AIAA Journal, 1994, 32(12): 2387-2393. DOI: 10.2514/3.12304

PALHARINI R C, SANTOS W F N. The impact of the length-to-depth ratio on aerodynamic surface quantities of a rarefied hypersonic cavity flow[J]. Aerospace Science and Technology, 2019, 88: 110-125. DOI: 10.1016/j.ast.2019.03.007

GUO G M, LUO Q. Flowfield structure characteristics of the hypersonic flow over a cavity: from the continuum to the transition flow regimes[J]. Acta Astronautica, 2019, 161: 87-100. DOI: 10.1016/j.actaastro.2019.05.023

PALMER G, ALTER S, EVERHART J, et al. CFD validation for long and short cavity flow simulations[C]// 39th AIAA Thermophysics Conference, Miami, Florida. Reston, Virigina: AIAA, 2007.

DONG H, LIU S C, CHENG K M. Review of hypersonic boundary layer transition induced by roughness elements[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(6): 1-15 (in Chinese).

WHEATON B M, BARTKOWICZ M D, SUBBAREDDY P K, et al. Roughness-induced instabilities at Mach 6: A combined numerical and experimental study[C]// 41st AIAA Fluid Dynamics Conference and Exhibit, Honolulu, Hawaii. Reston, Virigina: AIAA, 2011. doi: 10.2514/6.2011-3248

ALBERTO FRANCO SUMARIVA J, HEIN S, VALERO E. On the influence of two-dimensional hump roughness on laminar-turbulent transition[J]. Physics of Fluids, 2020, 32(3): 034102. DOI: 10.1063/1.5131577

BREHM C, DACKERMANN T, GRYGIER F, et al. Numerical investigations of the influence of distributed roughness on blasius boundary layer stability[C]// 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Orlando, Florida. Reston, Virigina: AIAA, 2011. doi: 10.2514/6.2011-563

GASTER M. The influence of roughness on boundary layer stability[M]// Solid mechanics and its applications. Dordrecht: Springer Netherlands, 2006: 125−134. doi: 10.1007/978-1-4020-4150-1_12

WU X S, DONG M. A local scattering theory for the effects of isolated roughness on boundary-layer instability and transition: transmission coefficient as an eigenvalue[J]. Journal of Fluid Mechanics, 2016, 794: 68-108. DOI: 10.1017/jfm.2016.125

LI C, DONG M. Impact of local cavities on evolution of the second-mode disturbances in hypersonic boundary layers[J]. journal of Aerospace Power, 2019, 34(10): 2203-2210.

DONG M, LI C. Effect of two-dimensional short rectangular indentations on hypersonic boundary-layer transition[J]. AIAA Journal, 2021, 59(7): 2368-2381. DOI: 10.2514/1.j059957

FEDOROV A V, MALMUTH N D, RASHEED A, et al. Stabilization of hypersonic boundary layers by porous coatings[J]. AIAA Journal, 2001, 39(4): 605-610. DOI: 10.2514/2.1382

FEDOROV A V. Receptivity of a high-speed boundary layer to acoustic disturbances[J]. Journal of Fluid Mechanics, 2003, 491: 101-129. DOI: 10.1017/s0022112003005263

FEDOROV A. Transition and stability of high-speed boundary layers[J]. Annual Review of Fluid Mechanics, 2011, 43: 79-95. DOI: 10.1146/annurev-fluid-122109-160750

DUAN L, WANG X W, ZHONG X L. Stabilization of a Mach 5.92 boundary layer by two-dimensional finite-height roughness[J]. AIAA Journal, 2013, 51(1): 266-270. DOI: 10.2514/1.j051643

CHEN S, LEE C B. Effect of cavity on hypersonic flat-plate boundary layer instability[J]. Physics of Fluids, 2021, 33(8): 084109. DOI: 10.1063/5.0059205

ZHAO L, DONG M, YANG Y G. Harmonic linearized Navier-Stokes equation on describing the effect of surface roughness on hypersonic boundary-layer transition[J]. Physics of Fluids, 2019, 31(3): 034108. DOI: 10.1063/1.5086912

PARK D, PARK S O. Study of effect of a smooth hump on hypersonic boundary layer instability[J]. Theoretical and Computational Fluid Dynamics, 2016, 30(6): 543-563. DOI: 10.1007/s00162-016-0396-7

PARK D, OH S. Effect of shape of two-dimensional smooth hump on boundary layer instability[J]. International Journal of Aeronautical and Space Sciences, 2020, 21(4): 906-923. DOI: 10.1007/s42405-020-00268-5

FONG K D, WANG X W, ZHONG X L. Numerical simulation of roughness effect on the stability of a hypersonic boundary layer[J]. Computers Fluids, 2014, 96: 350-367. DOI: 10.1016/j.compfluid.2014.01.009

FONG K D, ZHONG X L. DNS and PSE study on the stabilization effect of hypersonic boundary layer waves using 2-D surface roughness[C]// 46th AIAA Fluid Dynamics Conference, Washington, D. C. . Reston, Virginia: AIAA, 2016. doi: 10.2514/6.2016-3347

DONG M, ZHAO L. An asymptotic theory of the roughness impact on inviscid Mack modes in supersonic/hypersonic boundary layers[J]. Journal of Fluid Mechanics, 2021, 913: A22. DOI: 10.1017/jfm.2020.1146

LI S T, DONG M. Verification of local scattering theory as is applied to transition prediction in hypersonic boundary layers[J]. Advances in Mechanics, 2021, 51(2): 364-375(in Chinese).

HAN S B, LUO Y, LI H, et al. Data-driven and physical property-based hydro-acoustic mode decomposition[J]. Physics of Fluids, 2022, 34(2): 026102. DOI: 10.1063/5.0079906

WAN B B, LUO J S, SU C H. Response of a hypersonic blunt cone boundary layer to slow acoustic waves with assessment of various routes of receptivity[J]. Applied Mathematics and Mechanics, 2018, 39(11): 1643-1660. DOI: 10.1007/s10483-018-2391-6

MALIK M R. Prediction and control of transition in supersonic and hypersonic boundary layers[J]. AIAA Journal, 1989, 27(11): 1487-1493. DOI: 10.2514/3.10292

KONG W X, YAN C, ZHAO R. Effect of wall temperature on boundary layer transition prediction using transition model[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(10): 2249-2255(in Chinese).

SOUDAKOV V G, FEDOROV A V, EGOROV I V. Stability of high-speed boundary layer on a sharp cone with localized wall heating or cooling[C]//Proc of the Progress in Flight Physics - Volume 7, Munich, Germany. Les Ulis, France: EDP Sciences, 2015: 569-584. doi: 10.1051/eucass/201507569

DENG X G, MAO M L, TU G H, et al. High-order and high accurate CFD methods and their applications for complex grid problems[J]. Communications in Computational Physics, 2012, 11(4): 1081-1102. DOI: 10.4208/cicp.100510.150511s

ZHANG H X, ZHANG L P, ZHANG S H, et al. Some recent progress of high-order methods on structured and unstructured grids in CARDC[J]. Computers Fluids, 2017, 154: 371-389. DOI: 10.1016/j.compfluid.2016.10.006

MACK L M. Boundary-Layer linear stability theory [R]. California: California Inst of Tech Pasadena Jet Propulsion Lab, 1984.

LIN C C. The theory of hydrodynamic stability[J].The Mathematical Gazette, 1957, 41(337): 223-224.

TU G H, YANG Q, CHEN J Q, et al. Preliminary conception and test of global stability decomposition for flow stability analysis [C]// 10th International Conference on Computational Fluid Dynamics (ICCFD10), Barcelona, Spain , 2018.

TANG Q, ZHU Y D, CHEN X, et al. Development of second-mode instability in a Mach 6 flat plate boundary layer with two-dimensional roughness[J]. Physics of Fluids, 2015, 27(6): 064105. DOI: 10.1063/1.4922389

LIU K P, LUO J S. Effect of concave groove on the stability of boundary layer[J]. Journal of Aerospace Power, 2016, 31(1): 168-178(in Chinese).

XU X G, XU G L, WANG X T, et al. Review of bidimensional Hilbert transform[J]. Communications Technology, 2016, 49(10): 1265-1270(in Chinese).

GAVISH M, DONOHO D L. The optimal hard threshold for singular values is 4 sqrt 3[J]. IEEE Transactions on Information Theory, 2014, 60(8): 5040-5053. DOI: 10.1109/TIT.2014.2323359

LUO Y, LI H, HAN S B, et al. Direct numerical simulations of self-sustained oscillations in two-dimensional open cavity for subsonic and supersonic flow[J]. Advances in Applied Mathematics and Mechanics, 2021, 13(4): 942-965. DOI: 10.4208/aamm.oa-2020-0232

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