二维超音速激波风洞及其应用  

TWO DIMENSIONAL SUPERSONIC SHOCK TUNNEL AND ITS APPLICATION

作　　者：王世芬[1] 王宇[1] 唐贵明[1] 李振华[1] 刘鹏[1] 

机构地区：[1]中国科学院力学研究所

出　　处：《航空学报》1994年第11期1379-1382,共4页Acta Aeronautica et Astronautica Sinica

摘　　要：简述了二维超音速激波风洞的设计要点和性能，并给出在该风洞中低凸台诱导激波和湍流边界层相互作用的实验结果。实践表明：在被驱动段和喷管之间安装一个前缘光滑的矩形剖面短管道；并将二维喷管精加工成型，就能获得实验所需的均匀超音速气流。A brief description is given of design and performanee of a two dimensional supersonic shock tunnel.The experimental results of three dimensional interaction between shock wave and trubulent boundary layer indueed by low protuberance are presented.Current experience indi-cates that the use of a rectangular tunnel with round leading edge from driven tube end to two dimensional nozzle entrance,when coupled with precisely manufactured contoured nozzle,can generate a unifonn supersonic flow which is generally adequate for aerodynamics testing.

关 键 词：激波风洞 激波干扰 分离流 压力测量 热流 

分 类 号：V211.751[航空宇航科学与技术—航空宇航推进理论与工程] O357.42[理学—流体力学]