Control of Stalled Flow over an Airfoil by Acoustic Excitation of Vortices.
Control of Stalled Flow over an Airfoil by Acoustic Excitation of Vortices.
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通过涡声激励控制翼型上的失速流。
DOI：
10.2322/jjsass1969.43.53
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发表时间：
1995
期刊：
影响因子：
--
通讯作者：
S. Furumoto
中科院分区：
文献类型：
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作者：
M. Nishioka;M. Asai;S. Furumoto
我们一直致力于边界层分离，特别是涡激控制。在本文中，声学强迫应用于 NACA0015 翼型上的分离流，以控制高攻角下的边界层分离。结果表明，即使在19°攻角下，通过声学激发强涡流也能成功抑制分离气泡。激发涡流规模与分离气泡高度之间匹配的重要性，在我们之前关于平板翼型前缘分离的声学控制的实验中已经提出，本实验也支持了这一点。
We have been working on the boundary layer separation, in particular its control by vortex excitation. In this paper, acoustic forcing is applied for the separated flow over a NACA0015 airfoil to control the boundary layer separation at high angle of attack. The results show that the separation bubble can be successfully suppressed even at angle of attack 19° through exciting strong vortices acoustically. The importance of the matching between the scale of the excited vortices and the separation bubble height, which has been suggested in our previous experiment on the acoustic control of the leading-edge separation of a flat-plate airfoil, is also supported by the present experiment.