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基于涡系相交不稳定性的飞机尾流控制方法

鲍锋 刘锦生 朱睿 江建华 王俊伟

鲍锋, 刘锦生, 朱睿, 等 . 基于涡系相交不稳定性的飞机尾流控制方法[J]. 北京航空航天大学学报, 2015, 41(8): 1381-1387. doi: 10.13700/j.bh.1001-5965.2014.0806
引用本文: 鲍锋, 刘锦生, 朱睿, 等 . 基于涡系相交不稳定性的飞机尾流控制方法[J]. 北京航空航天大学学报, 2015, 41(8): 1381-1387. doi: 10.13700/j.bh.1001-5965.2014.0806
BAO Feng, LIU Jinsheng, ZHU Rui, et al. Control method for aircraft wake vortex based on Rayleigh-Ludwig instability[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(8): 1381-1387. doi: 10.13700/j.bh.1001-5965.2014.0806(in Chinese)
Citation: BAO Feng, LIU Jinsheng, ZHU Rui, et al. Control method for aircraft wake vortex based on Rayleigh-Ludwig instability[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(8): 1381-1387. doi: 10.13700/j.bh.1001-5965.2014.0806(in Chinese)

基于涡系相交不稳定性的飞机尾流控制方法

doi: 10.13700/j.bh.1001-5965.2014.0806
基金项目: 国家自然科学基金(11072206)
详细信息
    通讯作者:

    鲍锋(1961-),男,辽宁营口人,教授,fbao@xmu.edu.cn,主要研究方向为实验流体力学、尾流控制.

  • 中图分类号: V211.76

Control method for aircraft wake vortex based on Rayleigh-Ludwig instability

  • 摘要: 在飞机飞行的过程中尾涡会伴随着升力产生,威胁后机的飞行安全.在简化机翼模型上添加扰流片,通过一个矩形翼以引入一个与主翼尾涡大小不同、方向相反的小涡,构建尾流自消散四涡系统,以期诱发尾涡的Rayleigh-Ludwig相交不稳定性.通过改变扰流片的大小形状,调整模型的攻角和拖曳速度,采用粒子图像速度场仪测量系统定量研究在低雷诺数下单主翼尾涡发展特性以及双涡相互作用特性.研究表明:在未添加扰流片时,尾涡环量在45个翼展内相对于初始环量基本保持不变;在添加扰流片的情况下尾涡的环量衰减可以达到35%~55%,而未添加的基本翼型的尾涡的环量则几乎保持不变,这说明添加适当的扰流片能诱发尾涡的Rayleigh-Ludwig相交不稳定性,加速尾涡的消散,当小涡和主涡的初始环量比为-0.489、初始距离比为0.5时,45个翼展范围内,尾涡环量衰减55.9%.本文系统性的实验结果可以为低尾流机翼的设计提供参考依据.

     

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出版历程
  • 收稿日期:  2014-12-22
  • 网络出版日期:  2015-08-20

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