采用块结构网格与二阶精度流场分区求解技术，对固体火箭冲压发动机增程弹丸超声速进气道特性进行了深入研究。
By means of block structure grid and second-order zonal solver method, the research on supersonic inlet performance of solid rocket ramjet assisted range projectiles was carried out.
流动计算采用了多块分区运动网格技术。
Moving grid-strategy and multi-block grids technology were used in the calculation.
讨论了三维非结构混合网格区域分解技术及子分区显示技术。
Advanced techniques of data structure for 3d unstructured hybrid mesh domain decomposition and sub-domain display are presented.
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