翼尖襟翼机翼的空气动力学特性

2019/01/15   下载量： 5 次

方案摘要

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应用领域 航空航天
检测样本 航空
检测项目
参考标准 暂无

采用两台Phantom 9.1v 型高速相机和双帧双脉冲YAG激光器，以及LaVision的DaVis8.3.0软件构成2D3C粒子成像测速系统。对风洞中的震动翼尖襟翼的空气动力学特性进行了测量研究。

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In the present study, an oscillating membrane flapper was pivotally attached to the tip
of a conventional rigid wing. Stroke-averaged aerodynamic forces were measured for the range of the flapping frequency, showing significant increases in the lift coefficient and lift-to-drag ratio for the wing with a flapper. Major vortex patterns were deduced from observations of smoke-wire visualization and 2D phase-locked particle image velocimetry (PIV). The centerline of the primary vortex wanders in the counterclockwise direction. On the contrary, its core rotates in the same sense of rotation as a wingtip vortex in a conventional wing. The secondary weaker vortex of opposite rotation lasts for a half stroke. The vortex ring sheds from the flapper during the second half of the upstroke and pronation. The outer parts of the vortex system are much stronger than the inner ones. The circulation and size of vortices decrease significantly at the most distant station from the wing. Strong vertical jets were found in smoke-wire visualization and confirmed with velocity and vorticity fields obtained by PIV. These jets are formed between undulating vortices and inside of the vortex ring. The jet airflow moves away from the flapper and downward or upward depending on the flapping direction.

上一篇 在一个双稳湍流涡旋火焰中，对间歇性动态的时间-频率定位
下一篇 S型进气道流动扰动的非稳定特性

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北京欧兰科技发展有限公司
金牌会员 丨 第17年
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