翼型
失速(流体力学)
阻力
NACA翼型
空气动力学
机械
攻角
升阻比
雷诺数
升力诱导阻力
风洞
航空航天工程
流量控制(数据)
物理
工程类
湍流
电信
作者
Hocine Tebbiche,M.S. Boutoudj
出处
期刊:International journal of fluid mechanics research
日期:2021-01-01
卷期号:48 (2): 29-46
被引量:3
标识
DOI:10.1615/interjfluidmechres.2021036842
摘要
Flow control is a very promising solution for improving the performance of aerial and terrestrial vehicles. Among the various existing techniques, blowing is effective in reducing or delaying the detachment near a wall by restoring energy to the moving fluid. The control solution proposed in this work relates to steady blowing through a micro-hole series in the case of an NACA 0015 airfoil and a simplified Ahmed body geometry. An experimental study was conducted in a subsonic wind tunnel for several incidences of the airfoil, two inclinations of the Ahmed body rear window, and a range of flow speeds (15-30 m/s). The investigation also took into account the effect of the blowing flow rate and the Reynolds number. The results showed interesting improvements in aerodynamic coefficients. Indeed, for a rear window tilted 20° in the case of Ahmed body, a reduction in drag of 3.6% is reached when applying minimum blowing with Cμ = 0.28%, whereas 15% is obtained by complete blowing at Cμ = 4.79%. On the other hand, at a high-drag regime corresponding to a 30° rear window slant, a 19% drag reduction is achieved with Cμ = 5%. As for the NACA 0015 airfoil, an improvement in lift of around 49%, a significant decrease in drag by 69%, and a delay in stall by 4° are obtained.
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