Research on flow drag reduction based on the bionic structure of dragonfly wings
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摘要:
为了实现有效减阻，基于蜻蜓翅翼管状翅脉结构设计出一种圆弧形凹槽仿生结构，通过对比研究不可压缩平板原型及改型方案流场中的减阻相关参数及湍流特性，明确仿生结构设计参数对流场阻力特性及边界层转捩起始位置的影响规律。研究结果表明：仿生结构布置位置、几何尺寸参数及凹槽列数对流场的影响作用规律性明显；同时也发现凹槽列间隔在小于等于槽宽尺寸范围内作用效果相近，于转捩位置前20%流向长度区域处进行0.75 mm深尺寸方案的圆弧形凹槽结构的布置引入了外部扰动，使原有的层流边界层速度剖面更饱满，抗干扰能力进一步增强，从而推迟转捩发生，以此增加层流覆盖区域实现有效减阻；理想方案相较于原型可增加10.75%流向长度范围被层流覆盖，降低约6.38%的摩擦阻力。
Abstract:In order to achieve effective drag reduction, a bionic structure with a circular arc groove was designed based on the dragonfly wing tubular vein structure. By comparing the drag reduction related parameters and turbulence characteristics in the flow field of the incompressible-plate prototype and the modified scheme, the influences of the design parameters of the bionic structure on the resistance characteristics of the flow field and the starting position of the boundary layer transition were determined. The results showed that the arrangement of the bionic structure, the geometric size parameters and the number of groove rows affected the flow field regularly. At the same time, it was also found that the groove spacing had a similar effect on the range of size less than or equal to the groove width. The arrangement of the circular arc groove structure with a 0.75 mm deep size scheme at the first 20% flow direction length region of the transition position introduced external disturbances, which made the original laminar boundary layer velocity profile fuller and the anti-interference ability further enhanced, thus delaying the transition. In this way, the laminar flow coverage area was increased to achieve effective drag reduction. Compared with the prototype, the ideal scheme can increase 10.75% of the flow direction length range covered by laminar flow, and reduce about 6.38% of the friction resistance.
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Key words:
- transition /
- groove /
- laminar flow drag reduction /
- dragonfly wings /
- bionic non-smooth surface
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图 9 原型及单列凹槽改型平板总阻力分布图
Figure 9. Total resistance distribution diagram of original slab and single row groove arrangement scheme modification
图 10 不同位置单列凹槽湍流强度云图
Figure 10. Contour of turbulence intensity with single row groove at different positions
图 11 位置2处原型及改型摩阻系数分布图
Figure 11. Friction coefficient distribution diagram of the original and modified at position 2
图 12 位置2处各尺寸凹槽湍流强度云图
Figure 12. Contour of turbulence intensity for grooves of different size at position 2
图 14 原型及改型摩阻系数分布图
Figure 14. Original slab and modification friction coefficient distribution diagram
图 16 位置2处延迟转捩方案湍流强度分布图
Figure 16. Turbulence intensity distribution diagram of delayed transition scheme at position 2
图 17 多列设计方案总阻力分布图
Figure 17. Total resistance distribution diagram of multi-column design scheme
图 18 变间隔6列凹槽方案摩阻系数分布图
Figure 18. Friction coefficient distribution diagram of variable gap six row grooves scheme
图 20 原型及改型间歇因子云图
Figure 20. Intermittency factor contour of original slab and modification
图 21 原型及改型位移厚度分布图
Figure 21. Displacement thickness distribution diagram of original slab and modification
图 22 原型及改型动量厚度分布图
Figure 22. Momentum thickness diagram of original slab and modification
图 23 原型及改型形状因子分布图
Figure 23. Shape factor distribution diagram of original slab and modification
图 24 原型及改型不同位置速度剖面图
Figure 24. Profile of velocity at different positions of original slab and modification
表 1 流向位置设定表
Table 1. Table of flow direction position setting
位置 基于板长的
流向雷诺数$ R{e}_{x} $加前缘后
流向位置x/mm1 0 25 2 3.75×105 179 3 7.5×105 333 4 1.125×106 488 5 1.5×106 642 
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