超声速主流中横向喷流场的激波-旋涡结构的数值模拟  

NUMERICAL SIMULATION OF A JET INTERACTING WITH A SUPERSONIC CROSSFLOW

作　　者：张涵信 刘君 

机构地区：[1]中国空气动力力研究与发展中心

出　　处：《空气动力学学报》1991年第1期8-13,共6页Acta Aerodynamica Sinica

基　　金：中国自然科学基金

摘　　要：本文利用NND格式,通过求解NS方程,对二维超声速主流中横向喷流干扰流场进行了数值模拟,计算清楚地给出了激波结构、回流区和混合层。本文计算得到的激波结构和实验相当一致。最有兴趣的是由于喷流的干扰,主流在喷口前发生主涡分叉,观察到三个流向旋转涡和两个反流向旋转涡;在喷口后的背风区,存在具有低压和回流区的尾迹。The interaction of a jet and a supersonic crossflow has been simulated by solving Navier-Stokes equations with NND scheme which is a non-oscillatory, containing no free parameters and dissipa-tive finite difference scheme [1]. The results clearly depict the shock structure, recirculation regions and the mixing layer.The shock structure obtained in this paper agrees well with the experiment [2]. The most interesting characteristics of calculated flow is the bifurcations of the primary votex in front of the injector due to the interaction of the jet and the crossflow. Three streamwise rotating vortices and two countcrrotating vortices can be observed. A wake flow with relatively lower pressure and recirculation zone exists on the lee side of the injector.

关 键 词：横向喷流 激波 旋涡 超声速流 模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]