关键词: 激波风洞, 激波干扰, 分离流, 压力测量, 热流

Abstract: 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.

Key words: shock tubes, shock wave interaction, separated flow, pressure measurement, heat flow