An experimental study of cold flow field was conducted under entrance Mach number 2.5 on a supersonic combustor experiment rig with subsonic pilot combustor and stream wise vortices mixer.

• 摘要结合对应的数值计算，对一种带亚声速预燃室和流向涡掺混器的超声速燃烧模型燃烧室实验台，在其进口马赫数为2.；5的来流条件下，进行了冷态流场的实验研究。