Compressible dynamic stall control using high momentum microjets
Compressible dynamic stall control using high momentum microjets
复制标题
使用高动量微射流的可压缩动态失速控制
DOI：
10.1007/s00348-014-1813-6
复制
发表时间：
2014
影响因子：
2.4
通讯作者：
M. Chandrasekhara
中科院分区：
文献类型：
--
作者：
James J. Beahan;C. Shih;A. Krothapalli;Rajan Kumar;M. Chandrasekhara
在NASA艾姆斯可压缩动态失速实验装置上对NACA 0015翼型周期性俯仰运动的动态失速过程控制进行了实验研究。多个微射流喷嘴均匀分布在翼型前缘前12%的弦长处，用于动态失速控制。点衍射干涉技术被用来定性和定量地表征控制效果。已经发现微喷控制在抑制动态失速涡的出现和在整个迎角范围内的相关的大规模流动分离方面是非常有效的。在高马赫数（M = 0.4）时，微射流的使用似乎消除了引起激波诱导分离的激波结构，从而证实了使用微射流在控制具有强压缩性效应的动态失速方面是有效的。一般而言，微射流控制在维持前缘吸入压力和防止流动分离方面具有总体积极效果。
Control of the dynamic stall process of a NACA 0015 airfoil undergoing periodic pitching motion is investigated experimentally at the NASA Ames compressible dynamic stall facility. Multiple microjet nozzles distributed uniformly in the first 12 % chord from the airfoil’s leading edge are used for the dynamic stall control. Point diffraction interferometry technique is used to characterize the control effectiveness, both qualitatively and quantitatively. The microjet control has been found to be very effective in suppressing both the emergence of the dynamic stall vortex and the associated massive flow separation at the entire operating range of angles of attack. At the high Mach number (M = 0.4), the use of microjets appears to eliminate the shock structures that are responsible for triggering the shock-induced separation, establishing the fact that the use of microjets is effective in controlling dynamic stall with a strong compressibility effect. In general, microjet control has an overall positive effect in terms of maintaining leading edge suction pressure and preventing flow separation.