粗糙元对高超声速边界层转捩影响的研究进展

董昊; 刘是成; 程克明

doi:10.11729/syltlx20180167

粗糙元对高超声速边界层转捩影响的研究进展

doi: 10.11729/syltlx20180167

南京航空航天大学航空宇航学院, 南京 210016

基金项目:

国家自然科学基金项目 11872208

装备预研领域基金项目 61402060301

详细信息

作者简介:
董昊(1983-)，男，河南偃师人，博士，副教授。研究方向：高超声速风洞实验、边界层转捩。通信地址：江苏省南京市秦淮区御道街29号空气动力学系(210016)。E-mail:donghao@nuaa.edu.cn

通讯作者:
董昊, E-mail:donghao@nuaa.edu.cn

中图分类号: O354.4
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- 文章访问数: 508
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- 被引次数: 0
出版历程
- 收稿日期: 2018-10-30
- 修回日期: 2018-12-14
- 刊出日期: 2018-12-25

Review of hypersonic boundary layer transition induced by roughness elements

College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 高超声速边界层转捩对高超声速飞行器气动设计具有重要影响。转捩控制一直是转捩研究的主要目的之一，在高超声速情况下主要采用粗糙元进行边界层转捩控制。回顾了近年来不同类型粗糙元对高超声速边界层转捩影响及控制的最新研究进展；从粗糙元对高超声速边界层的感受性问题以及横流失稳影响的角度，介绍了其在高超声速边界层转捩机理相关研究中的作用；简要介绍了南京航空航天大学高超声速风洞（NHW）的油膜干涉测量技术在粗糙元诱导的高超声速边界层转捩研究中的应用；讨论了当前粗糙元对高超声速边界层转捩影响研究存在的问题，展望了该研究未来发展趋势。
- 粗糙元 /
- 高超声速 /
- 边界层转捩 /
- 转捩控制 /
- 感受性 /
- 横流失稳
Abstract: Hypersonic boundary layer transition plays an important role in aerodynamic design of hypersonic vehicles. Transition control is always one of the main purposes of the transition research. In the hypersonic flow, the roughness element is used to control the boundary layer transition. Firstly, this paper reviews the latest researches in hypersonic boundary layer transition control by various types of roughness elements in recent years. Then, from the perspective of the receptivity of the roughness elements to the hypersonic boundary layer and the crossflow stability, the role of the roughness element in the study of the hypersonic boundary layer transition mechanism is introduced based on the effect of the roughness element on hypersonic boundary layer transition. The application of the oil film interferometry technique in the study of hypersonic boundary layer transition induced by roughness elements in the hypersonic wind tunnel of Nanjing University of Aeronautics and Astronautics (NHW) is also briefly introduced. Finally, the existing problems in hypersonic boundary layer transition are discussed, and the future research trend is also prospected.
- roughness elements /
- hypersonic /
- boundary layer transition /
- transition control /
- receptivity /
- crossflow instability

HTML全文

图 1 高超粗糙元分类

Figure 1. Hypersonic roughness elements classification

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图 2 粗糙元临界高度和有效高度^[22]

Figure 2. Critical height and effective height of roughness elements^[22]

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图 3 基于DMD的粗糙元尾迹模态显示((a), (b), (c)分别表示20、40和53kHz的3种扰动模态)^[29]

Figure 3. Visualization of different modes in the wake of roughness elements based on the DMD method(a, b, c respectively denote three disturbance modes of 20, 40 and 53kHz)^[29]

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图 4 粗糙元上下游瞬时PIV流场图^[33]

Figure 4. Instantaneous PIV flow field of upstream and downstream of roughness element^[33]

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图 5 圆柱凹腔引起的发卡涡结构^[39]

Figure 5. Hair-pin vortices induced by cylindrical cavity^[39]

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图 6 长方形凹腔引起的流向涡结构(左：－10°，右：－15°)^[40]

Figure 6. Streamwise vortices induced by rectangular cavity^[40]

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图 7 模型表面瞬时压力脉动场分布((a)没有涂层，(b)优化后的涂层，(c)传统涂层)^[51]

Figure 7. Instantaneous fluctuating pressure fields for (a) baseline case without porous coating, (b) optimized one, and (c) conventional one^[51]

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图 8 小钝度锥模型及其纹影图(Ma=10)^[54]

Figure 8. Small-bluntness model, (a) mounted in launch sabot and (b) model in flight at Ma=10^[54]

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图 9 大钝度锥模型及其纹影图(Ma=10)^[54]

Figure 9. Large-bluntness model, (a) mounted in launch sabot and (b) model in flight at Ma=10^[54]

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图 10 粗糙表面多腔效应和涡旋动力学效应^[57]

Figure 10. Illustration of the multiple-cavity effect and vortex dynamics over a rough surface^[57]

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图 11 随机粗糙壁面流线分布(绿色标记为分离区)^[58]

Figure 11. Streamline distribution on random rough wall (green marks separation zone)^[58]

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图 12 高超声速转捩影响因素示意图^[8]

Figure 12. Affecting factors of hypersonic transition^[8]

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图 13 高超声速边界层自由流、壁面粗糙度扰动感受性^[68]

Figure 13. The receptivity in a hypersonic flow induced by free-stream and surface roughness disturbance^[68]

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图 14 慢模态和粗糙元引起的压力波动^[83]

Figure 14. Pressure perturbations induced by mode S and surface roughness^[83]

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图 15 横流边界层速度型^[94]

Figure 15. Velocity profile of crossflow boundary layer^[94]

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图 16 不同粗糙元条件下的转捩位置^[106]

Figure 16. Transition locations induced by different roughness elements^[106]

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图 17 不同单位雷诺数对粗糙元抑制转捩的影响^[110]

Figure 17. Effect of Reynolds number on suppressing transition by roughness elements^[110]

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图 18 光滑平板油膜干涉图像及表面摩阻系数对比

Figure 18. Oil film interference image of smooth flat plate and comparison of surface skin friction coefficient

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图 19 三维圆柱形孤立粗糙元后油膜干涉条纹以及数值模拟结果对比

Figure 19. Oil film interference fringes and numerical simulation results after 3D cylindrical isolated roughness elements

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