| 飞机尾流控制的SPIV实验研究 |
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| 引用本文： | 黄烁桥,;申功斯,;Robert Konrath,;Carl F.v. Carmer,;Kompenhans Jürgen.飞机尾流控制的SPIV实验研究[J].气动实验与测量控制,2009(1):18-22. |
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| 作者姓名： | 黄烁桥 ;申功斯 ;Robert Konrath ;Carl F.v. Carmer ;Kompenhans Jürgen |
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| 作者单位： | [1]北京航空航天大学航空科学与工程学院流体所,北京100191; [2]Institute of Aerodynamics and Flow Technology,Germany Aerospace Center （DLR）, Gottingen, Germany |
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| 基金项目： | 基金项目：中德（BUAA＆DLR）国际合作基金 |
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| 摘 要： | 利用简化的飞机模型，通过改变尾翼的迎角及展弦比，试图建立一种能加速自我消亡的尾流涡系统。该实验在拖曳水槽中进行，运用SPIV（体视粒子图像测速技术）系统进行测量，获得了一系列空间切面的2D／3C（二维／三分量）数据，给出了三种不同尾翼情况（两种有尾翼情况及一种无尾翼情况）下的SPIV观测结果，并将这几种情况作了对比。
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| 关 键 词： | 尾流涡 SPIV Rayleigh-Ludwieg不稳定性 飞机模型 水槽 |
Experimental study of SPIV on controlling wake vortex |
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| Institution: | HUANG Shuo-qiao, SHEN Gong-xin, Robert Konrath, Carl F. v. Camer, Kompenhans Jürgen ( 1. Institute of Fluid Dynamics, School of Aeronautic Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;2. Institute of Aerodynamics and Flow Technology, Germany Aerospace Center (DLR), Gottingen, Germany) |
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| Abstract: | An experimental study with a simplified model was carried out to establish a self-destructing vortex wake by changing the attack angle and the aspect ratio of HTW （Horizontal Tail Wing）. A SPIV（Stereo- Particle Image Velocimetry） system was employed in a water towing tank to obtain the sets of 2D/3C（2D -2 dimentional field, 3C-three component velocity measurements） velocity field data in different special slices. The results from three kinds of tail settings （2 with and 1 without HTW） are exhibited and compared with each other. |
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| Keywords: | wake vortex SPIV Rayleigh-Ludwieg instability aircraft model water tank |
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