仿生减阻翼型的气动性能

张子良; 张明明

doi:10.13224/j.cnki.jasp.20200485

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仿生减阻翼型的气动性能

气动热力学与总体设计 | 更新时间：2025-04-07

- 仿生减阻翼型的气动性能
- Aerodynamic performance for bionic drag⁃reducing airfoil
- 航空动力学报 2021年36卷第8期页码：1740-1748
- 作者机构：
  
  1.中国长江三峡集团有限公司科学技术研究院，北京 100038
  2.中国科学院工程热物理研究所，北京 100190
- 作者简介：
  
  张子良（1990-），男，博士生，主要从事风力机空气动力学、风电场微观选址研究。
- 基金信息：
  
  国家自然科学基金(51736008);中国科学院洁净能源先导科技专项(XDA21050303)
- DOI：10.13224/j.cnki.jasp.20200485
  中图分类号：
- 稿件说明：
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张子良, 张明明. 仿生减阻翼型的气动性能[J]. 航空动力学报, 2021,36(8):1740-1748.

Ziliang ZHANG, Mingming ZHANG. Aerodynamic performance for bionic drag⁃reducing airfoil[J]. Journal of Aerospace Power, 2021, 36(8): 1740-1748.
张子良, 张明明. 仿生减阻翼型的气动性能[J]. 航空动力学报, 2021,36(8):1740-1748. DOI： 10.13224/j.cnki.jasp.20200485.

Ziliang ZHANG, Mingming ZHANG. Aerodynamic performance for bionic drag⁃reducing airfoil[J]. Journal of Aerospace Power, 2021, 36(8): 1740-1748. DOI： 10.13224/j.cnki.jasp.20200485.

摘要

利用一种基于滑移边界理论的仿生肋条结构的模化方法，对仿生减阻翼型的气动性能开展了数值模拟研究。结果显示：肋条结构同时布置在翼型压力面和吸力面湍流区域时，仿生减阻翼型的阻力可降低1.73%~3.07%，升阻比可提高2.10%~4.08%，其中黏性阻力的减小是总阻力下降的主要原因。对流场分析表明，仿生减阻翼型的速度曲线出现一定抬升，使得湍流边界层中的黏性子层增厚，进而导致了仿生减阻翼型气动性能的提升。

Abstract

By adopting a bionic riblet model based on the slip⁃boundary theory

the aerodynamic performance for the bionic drag⁃reducing airfoil was numerically investigated.The results suggest that the total drag of the bionic drag⁃reducing airfoil could reduce by 1.73%-3.07% and the lift⁃drag ratio could increase by 2.10%-4.08% when riblets are applied in turbulence regions of both pressure and suction surfaces.The main reason for the total drag reduction was attributed to the decrease of the viscous drag.Flow field analysis indicated that the velocity profile of the bionic drag⁃reducing airfoil had an uplift compared with the smooth airfoil

resulting in an increase of the viscous⁃sublayer thickness.The aerodynamic performance was then improved.

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references

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