微型涡流发生器与微射流涡流发生器组合流动控制研究  

Investigation on Flow Control Using Combination of Micro Vortex Generator and Vortex Generator Jet

作　　者：朱拥勇[1] 王旭东[1] ZHU Yongyong;WANG Xudong(Navy University of Engineering,Wuhan 430000,China)

机构地区：[1]海军工程大学,武汉430000

出　　处：《兵器装备工程学报》2018年第7期175-179,共5页Journal of Ordnance Equipment Engineering

基　　金：国家自然科学基金项目(11372350)

摘　　要：为延迟边界层分离以改善超声速进气道/隔离段性能,运用数值模拟方法研究来流马赫数2.0条件下微型涡流发生器与微射流涡流发生器组合的流动控制特性,着重比较了射流位置对流场的影响,分析了流场改善的原因。研究结果表明:较无射流控制,微型涡流发生器与射流组合能够极大提高隔离段的抗反压能力,射流后置的流动控制性能更佳;设置射流与微型涡流发生器的距离在一定区间内可以大幅度延迟角区低速回流区的形成,边界层抗分离性增强,流场畸变指数明显减小。The supersonic flow （Ma = 2.0） past micro-ramps and micro vortex generator jet have been simulated to suppress boundary layer separation and improve the characteristics of isolator. In this paper, the effects of jet positions on the flow field and the causes of flow field improvement were analyzed. The findings of the study are as follows, the combination of micro vortex generator and vortex generator jet allowed the isolator＇ s back pressure to be raised in a higher level, in comparison, vortex generator jet behind micro vortex generator had better effect. The formation of the back flow field could be delayed effectively by setting the distance between vortex generator jet and micro vortex generator in a rational region, the skewness coefficient decreased. Skewed angle had little effect on x axis position of back flow field, but changed the back flow scope and comer vortex greatly, in particularly. Decreasing the skewed angle are helpful to minish the skewness coefficient and total pressure coefficient. Key words： supersonic; isolator; flow control; micro vortex generator; vortex generator jet

关 键 词：超声速 隔离段 流动控制 微型涡流发生器 微射流涡流发生器 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]