火箭垂直发射系统燃气流场的计算

CALCULATION OF BURNING GAS FLOW IN THE VERTICAL LAUNCH SYSTEM OF A ROCKET

本文报导了火箭垂直发射系统燃气流场的数值计算结果，在计算中采用二阶精度的ＭＵＳＣＬ格式。为了将三维问题转化为二维问题，对数值流量作了校正。处理了弹体运动引起的动边界，分析了计算结果，与实验测量结果比较表明，数值精度是满意的。。

In this paper, the numerical results of burning gas flow in the vertical launch system of a rocket are reported. A second-order accurate MUSCL scheme is employed. Numerical flux-corrected is carried out in order that three dimensional flow can be converted into two dimensional case. Moving boundaries generated by the rocket body are treated, and the computed results is analyzed, which shows that the numerical accuracy is satisfied by comparing with experimental measurements.