| 直升机旋翼流场特性PIV试验分析 |
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| 引用本文： | 李春华,曹金华,吴裕平.直升机旋翼流场特性PIV试验分析[J].直升机技术,2012(1):6-10. |
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| 作者姓名： | 李春华 曹金华 吴裕平 |
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| 作者单位： | 1. 中航工业直升机设计研究所,江西景德镇,333001
2. 总参陆航部驻景德镇地区军事代表室,江西景德镇,333002 |
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| 摘 要： | 基于PIV技术对悬停和前飞状态的模型旋翼流场进行了试验研究,对比分析了不同前飞速度、总距、转速、方位等条件下的旋翼速度场和桨尖涡运动,获得了在悬停和前飞条件下旋翼流动特性,为旋翼非定常流动机理研究和桨叶气动设计提供试验支持.
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| 关 键 词： | 直升机 旋翼 流场试验 PIV |
PIV Experimental Investigation on Flow Field for Helicopter Rotor |
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| Authors: | LI Chunhua CAO Jinhua WU Yuping |
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| Institution: | 1(1.China Helicopter Research and Development Institute,Jingdezhen,333001,China;2.Army Aviation Representative Office of General Staff in Jingdezhen,Jingdezhen,333002,China) |
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| Abstract: | Particle Image Velocimetry technique(PIV)was applied to the experiments of flow field for model rotor for hover and forward flight.The geometries of blade tip vortex and distributions of induced velocities were measured for different advance ratio,collective pitch,rotational speed and azimuth angle,and the aerodynamic characteristics of rotor for hover and forward flight were obtained.The experimental results were foundations of the flow mechanism analysis and rotor blade design. |
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| Keywords: | helicopter rotor flow field experiment PIV |
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