Comparative Study of Aerodynamic and Aeroacoustic Behavior of Flat Plate Airfoils With Different Trailing Edge Geometry

IRPN: Science Pub Date : 2017-12-21 DOI:10.2139/ssrn.3101286
Uddipta Gautam, S. Jha, S. Narayanan, L. Kumarswamidhas
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Abstract

The present study compares the aerodynamic and aeroacoustic behavior of the flow past two flat plate airfoils; viz. blunted trailing edge and sharp trailing edge, having a fixed aspect ratio of 1.867. The study is performed experimentally showing variance in lift and drag at two different velocity of 20m/s and 30m/s and at different angles of attack, viz. 5°, 12°, 20°, 25°, 30°. All the models are prepared by mild steel and the studies are conducted using 300×300×1000 mm subsonic wind tunnel. Results show that the drag coefficient in sharp trailing edge reduces significantly by a maximum amount of 22%. The lift coefficient, however, does not change significantly. Uncertainty analysis performed shows that maximum percentage of uncertainty in each case is less than 5%. Aero acoustic measurement of the noise radiated by the trailing edge of the two flat plates is performed in a reflecting environment at a velocity of 20m/s and at two different angles of attack of 10° and 15° with ¼’’ inch far field microphone mounted near the trailing edge of the airfoil in the test section. The spectra obtained indicate that the noise from the sharp trailing edge is consistently lower than the blunt trailing edge. Thus, this paper adequately demonstrates the role of trailing edge in modifying the aerodynamic as well as aero acoustic characteristic.
不同后缘几何形状平板翼型气动与气动声学性能比较研究
本文比较了两种平面翼型气流的气动特性和气动声学特性;即钝尾缘和锐尾缘,固定长宽比为1.867。实验显示了在20m/s和30m/s两种不同速度下,以及在5°、12°、20°、25°和30°攻角下的升力和阻力变化。所有模型均由低碳钢制成,并在300×300×1000 mm亚音速风洞中进行了研究。结果表明,锐尾缘处的阻力系数最大可降低22%。而升力系数变化不大。所进行的不确定度分析表明,每种情况下的不确定度最大百分比小于5%。在反射环境下,以20m/s的速度,在10°和15°两种不同的迎角下,在试验段翼型后缘附近安装1 / 4英寸远场麦克风,对两个平板后缘辐射的噪声进行了气动声学测量。得到的频谱表明,尖锐后缘的噪声始终低于钝后缘的噪声。因此,本文充分展示了后缘在改变气动和气动声学特性方面的作用。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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