Experimental study of the effect of turbulence on a section model blade oscillating in stall
Experimental study of the effect of turbulence on a section model blade oscillating in stall
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DOI：
10.1002/we.137
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发表时间：
2004-10
期刊：
影响因子：
4.1
通讯作者：
X. Amandolese;E. Széchényi
中科院分区：
文献类型：
--
作者：
X. Amandolese;E. Széchényi
本文重点介绍了NACA 634 - 421翼型在雷诺数接近106和三种湍流度（1.1%、4.5%和7.5%）下的部分静、动截面模型试验。这些试验是在航空技术研究所的5 m × 3 m S4风洞中进行的，使用的试验装置迫使剖面模型在俯仰方向上振荡。采用迎风网格生成湍流强度较高的网格，其特征是湍流长度尺度小于翼型的弦长。翼型的静态特性是在攻角范围从0°到30°测量的。在动态试验中，使翼型绕前四分之一弦线在不同的平均迎角值（在静态失速区之下、之内和之外）、折合频率（范围从0·0183到0·183）和运动幅度（从2°到8°）下俯仰振荡。对于所有测试，气动载荷均通过非定常表面压力测量获得。分析了非定常升力、俯仰力矩和压力的分布，并着重讨论了来流运动特性和湍流度的影响。版权所有© 2004年约翰威利父子有限公司。
This article highlights part of the recent static and dynamic section model tests performed on a NACA 634_421 aerofoil for Reynolds numbers close to 106and three flow turbulence levels, 1·1%, 4·5% and 7·5%. These tests were conducted in the 5 m × 3 m S4 wind tunnel at the Institut AéroTechnique, using an experimental rig which forces the section model to oscillate in pitch. An upwind grid was used to generate the higher turbulence intensities characterized by turbulence length scales smaller than the chord of the aerofoil. The aerofoil's static characteristics were measured at angles of attack ranging from 0° to 30°. In the dynamic tests the aerofoil was made to oscillate in pitch around its fore quarter‐chord line at different values of mean angle of attack (below, in and beyond the static stall region), reduced frequency (ranging from 0·0183 to 0·183) and amplitude of motion (from 2° to 8°). For all tests the aerodynamic loads were obtained through unsteady surface pressure measurements. The unsteady lift, pitching moment and pressure distributions are analysed and the effects of both the motion characteristics and the turbulence level of the incident flow are highlighted. Copyright © 2004 John Wiley & Sons, Ltd.