Numerical study on the control of airfoil stall with bio-inspired herringbone groove array

被引：0
作者：
Zhang, Peng [1 ,2 ]
Cheng, Rixin [2 ]
Li, Yonghong [2 ]
Sun, Yigang [2 ]
机构：
[1] Key Laboratory of Civil Aircraft Airworthiness Technology, Civil Aviation University of China, Tianjin
[2] College of Aeronautical Engineering, Civil Aviation University of China, Tianjin
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2024年 / 39卷 / 11期
关键词：
additional losses; airfoil stall; flow control; herringbone groove array; vortex generator;
D O I：
10.13224/j.cnki.jasp.20230415
中图分类号：
学科分类号：
摘要：
Taking the NACA0012 airfoil as the research object, the control rules and physical mechanisms of bio-inspired herringbone groove array on airfoil stall were explored through numerical simulations. The herringbone groove array was placed on the airfoil's upper surface near the trailing edge, and the effects of groove depth and deflection angle on the control effectiveness were investigated. The results showed that different designs of herringbone groove array can effectively broaden the stable operating range of the airfoil, and the implementation of herringbone groove array with a depth of only 0.001 35 chord length and a deflection angle of 45°can increase the stable operating range by 28.57%. Detailed flow field analysis revealed that, due to the accumulation of small-scale vortices inside the grooves and the combined effect of the spanwise migration flow above the grooves, a pair of induced vortices with equal strength but opposite directions were formed near the airfoil's convergence lines. The induced vortices enhanced the mixing of the boundary layer with the mainstream flow, providing enough energy for the boundary layer to resist adverse pressure gradients under high angles of attack and effectively delaying airfoil stall. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
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