两串列扑翼的相位差对平均推力影响机理的实验研究

宫武旗; 贾博博; 席光

doi:10.6052/0459-1879-14-378

两串列扑翼的相位差对平均推力影响机理的实验研究

西安交通大学能源与动力工程学院, 西安 710049

基金项目: 国家自然科学基金资助项目(50676072).

详细信息

作者简介:
宫武旗,副教授,主要研究方向:流体机械气动力学及试验技术、湍流减阻、仿生翼流体动力学.E-mail:wqgong@mail.xjtu.edu.cn

中图分类号: V211.1
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出版历程
- 收稿日期: 2014-11-26
- 修回日期: 2015-08-26
- 刊出日期: 2015-11-17

AN EXPERIMENTAL STUDY ON THE INFLUENCE OF THE PHASE DIFFERENCE ON THE MEAN THRUST OF TWO PLUNGING WINGS IN TANDEM

Department of Fluid machinery and Engineering, School of Energy and Power Engineering, Xi'an Jiaotong University, Xi'an 710049, China

Funds: The project was supported by the National Natural Science Foundation of China (50676072).

摘要

摘要: 在一个低雷诺数的循环水洞中,实验研究了前后翅翼之间的相位差对两串列扑翼平均推力的影响.利用一个三分量的Kistler 压力传感器来测量扑翼的瞬时力;利用一个数字粒子测速仪系统(TSI DPIV) 来测量扑翼的前缘涡以及其周围的流场. 当相位差从0° 增加到360°,前翅的平均推力随着相位差正弦变化;前翅平均推力的增加是由于后翅的前缘涡和滞止区域增加了前翅的有效攻角. 后翅平均推力曲线有一个明显的V 字形低谷.低谷处较小的平均推力是由于前翅的脱落涡抑制了后翅前缘涡的形成并且减小了其有效攻角.当间距为0.5倍弦长相位差约为290°时,前后翅翼平均推力系数的合值能达到最大值0.667,明显大于两倍的单翼平均推力系数(2×0.255).
- 串列扑翼 /
- 扑翼相位差 /
- 水洞实验 /
- 平均推力 /
- 前缘涡
Abstract: An experimental study is performed to investigate the e ects of phase difference on the mean thrust coe cient of two wings in tandem undergoing a two-dimensional (2-D) plunging motion in a low Reynolds number water tunnel. A 3-D force sensor and a 2-D digital particle image velocimetry (DPIV) are used to measure the wing thrust force and leading edge vortex (LEV) around the wings, respectively. The mean thrust coe cient of the forewing follows a sinusoidal curve when the phase difference changes from 0° to 360°.The increase of the mean thrust coe cient of the forewing is caused by the LEV and stagnation region of the hindwing enhancing the jet velocity behind the forewing and its e ective angle of attack. The curve of the mean thrust coe cient of the hindwing has a V-shaped feature as the phase difference increases. The decreased coe cient in the bottom of the V-shaped curve is caused by the vortex shed from the forewing restraining the LEV formation of the hindwing and reducing its e ective angle of attack. When the spacing distance is half chord and phase difference is 290°, the combined mean thrust coe cient of the forewing and hindwing can reach the maximum value of 0.667, over twice the reference single wing value (2×0.255).
- plunging wings in tandem /
- phase difference /
- water tunnel experiment /
- mean thrust /
- leading edge vortex

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