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带前缘小翼的扇翼翼型气动特性数值模拟分析

杜思亮 冯衬 唐正飞

杜思亮, 冯衬, 唐正飞等 . 带前缘小翼的扇翼翼型气动特性数值模拟分析[J]. 北京航空航天大学学报, 2020, 46(5): 870-882. doi: 10.13700/j.bh.1001-5965.2019.0356
引用本文: 杜思亮, 冯衬, 唐正飞等 . 带前缘小翼的扇翼翼型气动特性数值模拟分析[J]. 北京航空航天大学学报, 2020, 46(5): 870-882. doi: 10.13700/j.bh.1001-5965.2019.0356
DU Siliang, FENG Chen, TANG Zhengfeiet al. Numerical simulation and analysis of aerodynamic characteristics of fan-wing airfoil with leading edge winglet[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(5): 870-882. doi: 10.13700/j.bh.1001-5965.2019.0356(in Chinese)
Citation: DU Siliang, FENG Chen, TANG Zhengfeiet al. Numerical simulation and analysis of aerodynamic characteristics of fan-wing airfoil with leading edge winglet[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(5): 870-882. doi: 10.13700/j.bh.1001-5965.2019.0356(in Chinese)

带前缘小翼的扇翼翼型气动特性数值模拟分析

doi: 10.13700/j.bh.1001-5965.2019.0356
基金项目: 

中国博士后科学基金 2018M642241

装备预研重点实验室基金 61422201180510

旋翼空气动力学重点实验室开放课题 RAL20190203

详细信息
    作者简介:

    杜思亮  男, 博士, 讲师。主要研究方向:空气动力学、飞行力学与控制

    冯衬  男, 硕士研究生。主要研究方向:空气动力学

    唐正飞  男, 博士, 副教授, 硕士生导师。主要研究方向:空气动力学、新概念无人飞行器

    通讯作者:

    杜思亮, E-mail: kjofchina@qq.com

  • 中图分类号: V211.52

Numerical simulation and analysis of aerodynamic characteristics of fan-wing airfoil with leading edge winglet

Funds: 

China Postdoctoral Science Foundation 2018M642241

Equipment Pre-research Key Laboratory Foundation 61422201180510

Rotor Aerodynamics Key Laboratory Foundation RAL20190203

More Information
  • 摘要:

    扇翼升力和推力的产生主要依靠翼型前缘弧形槽上方低压涡的形成,使得升力和推力具有较强的耦合关系,如何对其解耦控制是扇翼进一步工程应用的关键。对于扇翼翼型各项几何参数确定的情况下,前缘开口角的大小对扇翼气动性能的影响最大。因此考虑在基准扇翼翼型的前缘安装前缘小翼的方法来改变扇翼前缘开口角的大小,通过数值模拟的方法,对比分析了单片、双片和三片前缘小翼在不同前缘小翼偏转角、来流速度、迎角下对扇翼升力和推力的影响规律。结果表明:通过对前缘小翼偏转角的角度控制不仅仅可以改善扇翼的升力和推力,还可对低压涡的强度和位置进行控制,满足对扇翼气动力的主动控制要求,因而可实现对扇翼飞行器姿态进行操控的目的。

     

  • 图 1  扇翼二维翼型截面

    Figure 1.  Two-dimensional airfoil cross section of fan-wing

    图 2  扇翼前缘小翼设计

    Figure 2.  Design of leading edge winglet of fan-wing

    图 3  带单片前缘小翼的扇翼截面

    Figure 3.  Fan-wing cross section with single leading edge winglet

    图 4  网格生成

    Figure 4.  Mesh generation

    图 5  数值计算与试验结果对比

    Figure 5.  Comparison between numerical calculation and test results

    图 6  单片前缘小翼偏转角随迎角的变化曲线(v=12 m/s)

    Figure 6.  Variation curves of installation angle of single leading edge winglet with angle of attack(v=12 m/s)

    图 7  单片前缘小翼偏转角随来流的变化曲线(α=0°)

    Figure 7.  Variation curves of installation angle of single leading edge winglet with inflow(α=0°)

    图 8  单片前缘小翼的速度云图和流线图(v=12 m/s,α=0°)

    Figure 8.  Velocity contours and streamlines of single leading edge winglet(v=12 m/s, α=0°)

    图 9  单片前缘小翼的压力云图(v=12 m/s,α=0°)

    Figure 9.  Pressure contours of single leading edge winglet(v=12 m/s, α=0°)

    图 10  单片前缘小翼扇翼表面静压分布曲线(v=12 m/s,α=0°)

    Figure 10.  Static pressure distribution curves on surface of fan-wing with single leading edge winglet(v=12 m/s, α=0°)

    图 11  双片前缘小翼偏转角随迎角的变化曲线(v=12 m/s)

    Figure 11.  Variation curves of installation angle of double leading edge winglet with angle of attack(v=12 m/s)

    图 12  双片前缘小翼偏转角随来流的变化曲线(α=0°)

    Figure 12.  Variation curves of installation angle of double leading edge winglet with inflow(α=0°)

    图 13  双片前缘小翼的速度云图和流线图(前缘小翼偏转角为60°,α=0°)

    Figure 13.  Velocity contours and streamlines of double leading edge winglet(installation angle of leading edge winglet equals to 60°, α=0°)

    图 14  双片前缘小翼扇翼表面静压分布曲线(前缘小翼偏转角为60°,α=0°)

    Figure 14.  Static pressure distribution curves on surface of fan-wing with double leading edge winglet (installation angle of leading edge winglet equals to 60°, α=0°)

    图 15  三片前缘小翼偏转角随迎角的变化曲线(v= 12 m/s)

    Figure 15.  Variation curves of installation angle of three leading edge winglet with angle of attack(v=12 m/s)

    图 16  三片前缘小翼偏转角随来流的变化曲线(α=0°)

    Figure 16.  Variation curves of installation angle of three leading edge winglet with inflow(α=0°)

    图 17  三片前缘小翼的速度云图和流线图(v=12 m/s,α=0°)

    Figure 17.  Velocity contours and streamlines of three leading edge winglet(v=12 m/s, α=0°)

    图 18  三片前缘小翼的压力云图(v=12 m/s,α=0°)

    Figure 18.  Pressure contours of three leading edge winglet(v=12 m/s, α=0°)

    图 19  三片前缘小翼扇翼表面静压分布曲线(v=12 m/s,α=0°)

    Figure 19.  Static pressure distribution curves on surface of fan-wing with three leading edge winglet(v=12 m/s, α=0°)

    图 20  不同片数前缘小翼速度云图和流线图(前缘小翼偏转角为90°,v=12 m/s,α=0°)

    Figure 20.  Velocity contours and streamlines of different-number leading edge winglet (installation angle of leading edge winglet equals to 90°, v=12 m/s, α=0°)

    图 21  不同片数前缘小翼压力云图(前缘小翼偏转角为90°,v=12 m/s,α=0°)

    Figure 21.  Pressure contours of different-number leading edge winglet (installation angle of leading edge winglet equals to 90°, v=12 m/s, α=0°)

    图 22  不同片数前缘小翼静压分布与力变化曲线(前缘小翼偏转角为90°, α=0°)

    Figure 22.  Static pressure distribution and force variation curves of different-number leading edge winglet(installation angle of leading edge winglet equals to 90°, α=0°)

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出版历程
  • 收稿日期:  2019-07-03
  • 录用日期:  2019-10-11
  • 网络出版日期:  2020-05-20

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