| 倾转旋翼机流动机理及气动干扰特性试验 |
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| 引用本文： | 招启军,倪同兵,李鹏,张航,蒋霜,王博,林永峰.倾转旋翼机流动机理及气动干扰特性试验[J].航空动力学报,2018,33(12):2900. |
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| 作者姓名： | 招启军 倪同兵 李鹏 张航 蒋霜 王博 林永峰 |
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| 作者单位： | 1.南京航空航天大学 直升机旋翼动力学国家级重点实验室，南京 210016 |
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| 基金项目： | 国家自然科学基金（11572156） |
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| 摘 要： | 采用试验方法测量了悬停和过渡状态倾转旋翼机旋翼/机翼气动干扰特性，部分揭示了干扰流动的机理。基于3D-PIV(particle image velocimetry)技术的流场测量结果，发现大总距状态相对于小总距时倾转旋翼下洗流收缩更为剧烈，并有更强烈的卷起涡；揭示了“喷泉效应”的产生机理，受旋翼诱导作用的影响，“喷泉”中心的位置会随着总距和间距的改变而发生显著变化。测量了不同构型及状态参数对倾转旋翼/机翼之间气动干扰影响，发现减小垂直或水平距离均可使倾转旋翼升力有所增大，但将会增加机翼受到的旋翼下洗载荷。进行了该构型过渡状态气动干扰特性试验，获得旋翼、机翼综合气动特性与机翼攻角之间的影响关系，在较大机翼攻角时，将会加强对旋翼下洗流的阻碍作用，对旋翼起到类似“地面效应”的增升效果，但该现象随着机翼的偏转不断削弱；机翼升力随机翼段攻角增加呈现出先增大后减小的趋势。
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| 关 键 词： | 倾转旋翼机 流动机理 气动特性 喷泉效应 过渡状态 PIV技术 |
| 收稿时间： | 2017/10/11 0:00:00 |
Experiment on flow mechanism and aerodynamic interaction characteristics of tilt-rotor aircraft |
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| Abstract: | With use of experimental methods, aerodynamic interactional characteristics between rotor and wing of a tilt-rotor aircraft were measured both in hover and transition modes, partly revealing the interactional flow mechanism. The shrinking of rotor downwash was found to be more intense and roll-up vortex was more severe, in its large collective pitch states compared with the small one, based on the result of flow measurement via 3D-PIV (particle image velocimetry) technology. The generation mechanism of “fountain effect” was revealed and the position of “fountain” center influenced by the induced effect of rotor, varied visibly with the changes of collective pitch and the interval between rotor and wing. Then the aerodynamic interactions between rotor and wing in different configurations and state parameters were measured, and during the measurement, tilt-rotors lift was found to be increased either by reducing the vertical or horizontal distances of wind and rotor, bringing to wing the increasing downloads at the same time. A particular configuration at last was selected to perform an interaction experiment in its transition mode to obtain the relationship between the comprehensive aerodynamic characteristics of wing, rotor and the angle of attack of the wing. It is shown that, in large angles of attack of the wing, the encumbering effect of the wing on rotor downwash, acting as a lift-promoting effect on the rotor like “ground effect”, is promoted, but this effect is enervating with the turning of the wing; and the wing lift tends to go up firstly then down with the increase of the wing angles of attack. |
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| Keywords: | tilt-rotor aircraft flow mechanism aerodynamic characteristics fountain effect transition state PIV technology |
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