为了揭示含潜入喷管的固体火箭发动机尾部流动特征 ,按照几何相近和气动相似原则设计了通道为矩形的二维冷流实验模型 ,利用相位多普勒粒子分析仪 (PDPA)对燃烧室尾部气流的时均速度和湍流脉动速度进行了测量。实验结果表明气流在潜入喷管入口上游发生分离 ,再附点位于喷管前端部外侧 ,背壁空腔内形成一个较为稳定的回流区 ,流场的轴向和横向湍流强度都比较大 In order to reveal the tail flow characteristics of a solid rocket motor with submerged nozzles, a two-dimensional cold flow experimental model with rectangular passageway was designed according to the principle of geometric similarity and aerodynamic similarity. The phase-Doppler particle analyzer (PDPA) The mean velocity and turbulent pulsation velocity were measured. The experimental results show that the air flow separates upstream of the inflow nozzle. The point of attachment is located outside the front end of the nozzle. A relatively stable recirculation zone is formed in the cavity of the back wall, and the axial and transverse turbulence intensity of the flow field is relatively large