为了得到航弹母弹飞行稳定性及尾部流场特性,通过模拟试验和数值计算进行了研究.试验和模拟结果均表明该母弹飞行稳定,且两结果吻合较好.另外,采用数值计算对尾部流场进行了分析,得到了尾部压力分布特性,表明弹尾部存在涡流区,该区范围和流速随弹飞行速度的增加而增大. In order to obtain the flight stability of the missile and the characteristics of the tail flow field, the simulation experiments and numerical calculations are carried out.The results of the experiments and simulations show that the projectile flight stability, and the two results agree well with.In addition, The tail flow field was analyzed, and the tail pressure distribution was obtained. It showed that there was eddy current in the tail of the missile, and the range and flow velocity of the tail increased with the flight speed of the projectile.