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聚焦激光差分干涉法测量超/高超声速流动的进展

熊有德 余涛 薛涛 吴杰

熊有德,余涛,薛涛,等. 聚焦激光差分干涉法测量超/高超声速流动的进展[J]. 实验流体力学,2022,36(2):9-20 doi: 10.11729/syltlx20210126
引用本文: 熊有德,余涛,薛涛,等. 聚焦激光差分干涉法测量超/高超声速流动的进展[J]. 实验流体力学,2022,36(2):9-20 doi: 10.11729/syltlx20210126
XIONG Y D,YU T,XUE T,et al. Progress on focused laser differential interferometry in measuring supersonic/hypersonic flow field[J]. Journal of Experiments in Fluid Mechanics, 2022,36(2):9-20. doi: 10.11729/syltlx20210126
Citation: XIONG Y D,YU T,XUE T,et al. Progress on focused laser differential interferometry in measuring supersonic/hypersonic flow field[J]. Journal of Experiments in Fluid Mechanics, 2022,36(2):9-20. doi: 10.11729/syltlx20210126

聚焦激光差分干涉法测量超/高超声速流动的进展

doi: 10.11729/syltlx20210126
基金项目: 国家数值风洞(2018-ZT1A03);国家自然科学基金(92052301);中央高校基本科研业务费专项资金(2019kfyXKJC001)
详细信息
    作者简介:

    熊有德:(1993—),男,河南信阳人,博士研究生。研究方向:高超声速实验测量。通信地址:湖北省武汉市洪山区关山街道珞喻路1037号华中科技大学航空航天学院(430074)。E-mail:xiongyd@hust.edu.cn

    通讯作者:

    E-mail:jiewu@hust.edu.cn

  • 中图分类号: V211.74

Progress on focused laser differential interferometry in measuring supersonic/hypersonic flow field

  • 摘要: 聚焦激光差分干涉法(Focused Laser Differential Interferometry,FLDI)作为一种非介入式高时空分辨率的测试手段,适用于高超声速风洞等极端实验环境。从典型FLDI的光路设计出发,介绍了FLDI技术的测量原理以及空间滤波特性;梳理了近年来国内外研究者为满足不同气动问题的研究需求,对典型FLDI技术做出的一系列改进;介绍了FDLI技术在超声速以及高超声速流场(包括高超声速自由流来流扰动、高超声速边界层不稳定波与转捩以及超声速射流噪声辐射等)测量中的应用。本综述展现了FLDI技术在超声速以及高超声速流场测量中的潜力,为后续开展FLDI技术的改进及相关高超声速流场精密测量提供参考。
  • 图  1  FLDI系统的组成

    Figure  1.  Composition of FLDI system

    图  2  观测区双焦点示意

    Figure  2.  Schematic of the dual focus in the observation region

    图  3  光束分离引起的空间滤波

    Figure  3.  Spatial filtering caused by beam separation

    图  4  光强高斯分布引起的空间滤波

    Figure  4.  Spatial filtering caused by Gaussian distribution of light intensity

    图  5  切片归一化离散网格

    Figure  5.  Normalized discrete grid of slice

    图  6  FLDI敏感性测试结果[21]

    Figure  6.  Result of the FLDI sensitivity test[21]

    图  7  轴对称氦气射流的折射率均值场[22]

    Figure  7.  Average refractive index field of the axisymmetric He jet[22]

    图  8  FLDI响应的实验(蓝色)及数值计算(红色)结果对比[22]

    Figure  8.  Comparison of experimental (blue) and simulated (red) FLDI responses[22]

    图  9  FLDI动态响应[22]

    Figure  9.  Dynamic response of FLDI[22]

    图  10  CFLDI系统组成[25]

    Figure  10.  Schematic of the CFLDI setup[25]

    图  11  FLDI和CFLDI光束轮廓[24]

    Figure  11.  Beam profiles of FLDI and CFLDI systems[24]

    图  12  双测点FLDI光路示意[26]

    Figure  12.  Schematic of the two-point FLDI setup[26]

    图  13  LA-FLDI光束轮廓[32]

    Figure  13.  Beam profiles approaching the LA-FLDI system focal region[32]

    图  14  LA-FLDI系统组成[32]

    Figure  14.  LA-FLDI setup[32]

    图  15  实验数据与FLDI数值模拟结果对比[34]

    Figure  15.  Comparison between experimental data and FLDI simula-tion[34]

    图  16  FLDI数值模拟结果及对应的CFD得到的各发展阶段的瞬时密度场[34]

    Figure  16.  FLDI simulation and instantaneous flow field shown at several stages of development[34]

    图  17  安装屏蔽罩前后的归一化相位差功率谱[17]

    Figure  17.  Comparison of normalized phase difference spectra for runs with and without the beam shrouds installed[17]

    图  18  FLDI与皮托探头联合测量结果[17]

    Figure  18.  Combined measurement result of FLDI and Pitot probe[17]

    图  19  喷嘴下游不同截面脉动归一化RMS[39]

    Figure  19.  The normalized RMS of the pulsation of different cross-sections downstream of the nozzle[39]

    图  20  热线风速仪与FLDI频谱比较[39]

    Figure  20.  Comparison of hot wire anemometer and FLDI spectrum[39]

    图  21  归一化边界层密度脉动谱[24]

    Figure  21.  Normalized density fluctuations spectra inside the boundary layer[24]

    图  22  FLDI与PCB压力传感器测量裙锥表面不稳定波时间序列信号比较[14]

    Figure  22.  Time transient of FLDI and PCB flush mounted on the cone model[14]

    图  23  FLDI与PCB压力传感器测量尖锥表面不稳定波频域信号比较[14]

    Figure  23.  Power spectral density comparison of FLDI and PCB result of instability modes[14]

    图  24  FLDI测量尖锥模型边界层不稳定波法向频谱特征[14]

    Figure  24.  Power spectral density of FLDI measurement across of hypersonic boundary-layer on sharp cone model[14]

    图  25  双测点FLDI和皮托测得的速度剖面对比[38]

    Figure  25.  Comparison of velocity profiles measured by dual points FLDI and Pitot[38]

    图  26  CFLDI测得的平板第二模态不稳定波[29]

    Figure  26.  The second-mode instability wave of the flat plate measured by CFLDI[29]

    图  27  来流马赫为1.5的超声速射流平台

    Figure  27.  Mach 1.5 supersonic jet platform

    图  28  FLDI和麦克风测得的频谱对比

    Figure  28.  Comparison of spectra measured by FLDI and microphone

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出版历程
  • 收稿日期:  2021-09-22
  • 录用日期:  2021-11-18
  • 修回日期:  2021-11-03
  • 网络出版日期:  2022-01-07
  • 刊出日期:  2022-04-25

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