Abstract: Based on the 2-D axsiymmetric Euler equations, the complex flow field was computed for the supersonic flow around the body and rocket jet of inside bottom exhaust cavity. Domain decomposition method was applied. The Mach number was 2.0, and the attack angle was 0°. The results show that the flow structure is very clear, which include shock wave inside bottom exhaust cavity, and intersection shock and reflection shock induced by the interaction between rocket jet outside the bottom exhaust cavity and the supersonic flow. The results may provide theoretical foundation for the structure design and the aerodynamic characteristics.

Key words: Projectile aerodynamic characteristic;Gas flow;Flow distribution;Finite volume method;Numerical simulation

摘要： 从二维轴对称Euler方程出发,应用隐式有限体积TVD格式和分区技术数值模拟来流马赫数Ma=2 0,攻角α=0°时超声速绕流与底排装置空腔内的火箭燃气流相互干扰的复杂流场,计算得到了清晰的流场波系结构,包括底排装置空腔中的激波,火箭燃气流在底排装置空腔外底部与外来绕流作用后形成的相交激波、反射激波等,其结果可为底排火箭复合增程弹丸的结构设计和气动特性研究提供理论依据。

关键词: 弹丸气动特性;燃气流;流动分布;有限体积法;数值仿真