旋翼翼型激波/边界层干扰特性分析
CSTR:
作者:
作者单位:

1.南京航空航天大学直升机动力学全国重点实验室/直升机研究院,南京 210016;2.兰州理工大学能源与动力工程学院,兰州 730050

作者简介:

通讯作者:

招启军,男,教授,博士生导师,E-mail:zhaoqijun@nuaa.edu.cn。

中图分类号:

V211

基金项目:

国家自然科学基金(12032012);江苏高校优势学科建设工程资助项目。


Characteristics of Shock Wave/Boundary Layer Interactions on Rotor Airfoils
Author:
Affiliation:

1.National Key Laboratory of Helicopter Aeromechanics/Helicopter Research Institute, Nanjing University of Aeronautics & Astronautics, Nanjing 210016, China;2.College of Energy and Power Engineering, Lanzhou University of Technology, Lanzhou 730050, China

Fund Project:

  • 摘要
  • |
  • 图/表
  • |
  • 访问统计
  • |
  • 参考文献
  • |
  • 相似文献
  • |
  • 引证文献
  • |
  • 资源附件
  • |
  • 文章评论
    摘要:

    采用雷诺平均Navier-Stokes(Reynolds-averaged Navier-Stokes,RANS)方法结合基于当地变量的γ-Re?θt转捩模型,开展了旋翼翼型的激波/边界层干扰(Shock wave/boundary layer interaction,SWBLI)特性研究。重点关注了旋翼桨尖附近可能出现的SWBLI及其对气动特性和转捩特性的影响,并研究了气流参数对SWBLI的影响规律。结果表明:激波以及SWBLI引发的流动现象(例如激波后减速和流动分离)在一定程度上可以减小翼型的摩阻,但同时其自身会导致总阻力和升力特性的急剧恶化,力矩特性也会出现剧烈的变化。在本文的计算工况范围内,迎角、马赫数对SWBLI的影响较为显著,湍流度会对SWBLI造成一定程度的影响,而雷诺数对SWBLI的影响相对较小,各参数的影响机制及规律差别较大。

    Abstract:

    Utilizing the Reynolds-averaged Navier-Stokes (RANS) method in conjunction with a locally variable γ-Re?θt transition model, an in-depth investigation is conducted on the characteristics of shock wave/boundary layer interaction (SWBLI) for the rotor airfoil. This comprehensive study aims to unravel the intricate features of SWBLI in the vicinity of the rotor blade tip and decipher its implications on both aerodynamic and transition characteristics of rotor airfoils. Furthermore, a detailed exploration into the repercussions of flow parameters on the characteristics of SWBLI is undertaken. The findings reveal that the flow phenomena induced by shock waves and SWBLI, such as deceleration behind the shock wave and flow separation, can reduce the friction drag of airfoils to some extent. However, shock waves and SWBLI themselves can lead to a sharp deterioration in overall drag and lift characteristics, and also cause drastic changes in the moment characteristics. Within the confines of the computational conditions considered in this study, the angle of attack and Mach number have a significant impact on SWBLI. Turbulence intensity also has a certain degree of influence on SWBLI, whereas the Reynolds number has a relatively minor effect. The mechanisms and patterns of influence for each parameter vary considerably.

    参考文献
    相似文献
    引证文献
引用本文

杨柳青,赵国庆,王清,井思梦,马砾,招启军.旋翼翼型激波/边界层干扰特性分析[J].南京航空航天大学学报,2025,57(4):739-748

复制
相关视频

分享
文章指标
  • 点击次数:
  • 下载次数:
  • HTML阅读次数:
  • 引用次数:
历史
  • 收稿日期:2024-09-27
  • 最后修改日期:2025-01-03
  • 录用日期:
  • 在线发布日期: 2025-09-02
  • 出版日期:
文章二维码
您是第位访问者
网站版权 © 南京航空航天大学学报
技术支持:北京勤云科技发展有限公司