一种模拟喷管二维流场的新方法

A NEW METHOD TO SIMULATE THE TWO DIMENSIONAL FLOW IN NOZZLES

采用ＳＩＭＰＬＥ方法对固体火箭发动机喷管进行了纯气相流场的数值模拟。推导了建立在同位网格之上利用协变物理速度分量为计算变量的离散方程；采用协变物理速度分量推导压力修正方程；对密度采用一阶迎风格式插值，将ＳＩＭＰＬＥ方法扩大到计算可压流动。计算结果表明：本方法计算精度高，收敛速度快、程序编写简单。

IMPLE algorithm is presented for the two-dimensional compressible flow in solid propellant rocket nozzles.The covariant physical velocity components are applied as the primary dependent variables to deduce the differencial equations on the unstaggered grid system and also corrected-pressure equation.SIMPLE algorithmis developed for the compressible flow when one-order upwind scheme is applied for the density.The results show that this method improves the calculation accuracyand accelerates the convergent speed.