吹除法对斜激波/边界层干扰控制数值模拟  

Numerical simulation of the blowing method for controlling oblique shock/boundary layer interactions

作　　者：孙润鹏 朱卫兵[1] 黄舜[1] 陈宏[1] 

机构地区：[1]哈尔滨工程大学航天与建筑工程学院,黑龙江哈尔滨150001

出　　处：《哈尔滨工程大学学报》2012年第2期166-173,共8页Journal of Harbin Engineering University

摘　　要：为了对进气道内斜激波/边界层干扰进行控制,采用RSM模型,以二维平板/楔结构为基础,研究了斜激波冲击平板诱导边界层分离现象,探讨了吹除状态下流场波系结构和壁面参数分布,分析了吹除位置和总压对分离区及流场的影响.研究表明加入吹除控制之后,流场参数得到了有效改善,吹除喷嘴靠近分离区,吹除效果更好.吹除总压并不是越高吹除效果就越好,存在一个最佳吹除压力,该压力就是使吹除喷嘴出口气流达到近似音速,这一结论如进一步得到实验证实,对实际工程具有指导意义.In considering the existing shock wave/boundary layer interactions of the process control of supersonic in- lets, based on two-dimensional plate/wedge structure, a rational Reynolds stress model （RSM） turbulence model was used to study the turbulent boundary layer separation phenomenon by induction of an oblique shock wave im-pacting the flat-plate. An investigation into the wave structure of the flow field in a blowing state and the distribu- tion of the parameters along the wall was carried out, and the impact of the blowing position and total pressure on the flow field and separation zones was analyzed. Research shows that after injecting the blowing control, the flowfield parameters improve significantly. The closer the nozzle to the separation zones,the better the blowing effects, while the higher blowing total pressure is not the better one, and the best blowing pressure exists when the nozzle airflow is in a sonic condition. If confirmed, this conclusion has guiding significance for practical engineering.

关 键 词：吹除式边界层控制 激波 边界层 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]