燃烧室-喷管流场数值解

本文用时间相关法计算了固体火箭发动机燃烧室─喷管亚跨声速流场数值解，控制方程用ＭａｃＣｏｒｍａｃｋ二步显格式：边界点参数用物理边界条件和参考平面上的特征方程计算。计算表明，达到收敛的数值积分步数比纯喷管的跨声速计算要多得多。虽然喷管壁上和轴线上的马赫数分布与纯喷管计算类似，但喷管中的等马赫线分布与纯喷管计算的结果［３］相差较远。

Numerical Computation of Chamber-Nozzle Flowfield

The chamber-nozzle subsonic-transonic flowfield of solid rocket motor is computed by time-dependent method. The governing equations are numerically solved by MacCormack explicit scheme. The parameters of boundary points are calculated with physical boundary conditions and characteristic equations on the reference plane. It is shown that the numerical integral steps that have got to convergence for chamber-nozzle flowfield computation are much more than those for transonic nozzle flowfield calculation. Although the Mach number distribution along the wall and axis for chamber-nozzle flowfield is similar to that for transonic nozzle flowfield, the iso-Mach number line distribution doesn't agree with the transonic nozzle flowfield.