Abstract: In order to apply Block Implicit Algorithm(BIA)to the problems which have complicated boundaries, the computation grids were generated through an algebraic way, the boundary conditions of three dimensional steady state Navier Stokes equations were treated by modifying the discrete equations These methods were put into practices and were proved to be valid and efficient in the computations of flow fields in the chambers

Key words: Rocket ramjet;Boundary layer;Flow distribution;Numerical simulation;Block implicit algorithm

摘要： 针对实际复杂的补燃室结构和计算边界 ,以块隐式法计算流场 ,用代数法生成计算网格 ,通过改变离散方程来处理三维定常 N- S方程边界条件。算例表明 ,该方法正确可靠 ,迭代过程能够快速收敛。

关键词: 火箭冲压发动机;边界层;流动分布;数值仿真;块隐式法