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.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1994年第11期1379-1382,共4页
Acta Aeronautica et Astronautica Sinica
关键词
激波风洞
激波干扰
分离流
压力测量
热流
shock tubes,shock wave interaction,separated flow,pressure measurement,heat flow
