轴对称DCR进气分流流场数值模拟

用矢通量分裂法，采用ＭａｃＣｏｒｍａｃｋ二步格式，对ＤＣＲ（ＤｕａｌＣｏｍｂｕｓ－ｔｏｒＲａｍｊｅｔ，简称ＤＣＲ）进气分流流场进行了数值模拟，提供了全场清晰的波系结构和物理信息，计算结果表明，通过改变反应，可以有效地控制结尾激波的位置，从而改变亚燃室内回流区的大小，对组织亚燃室燃烧和火焰稳定创造良好的条件。

NUMERICAL SIMULATIONS OF AN AXISYMMETRIC DIVISION-FLOW INLET FIELD IN A DCR

The flux vector splitting method and MacCormack explicit two steps scheme is adopted and a numerical simulation is conducted on a division-flow inlet field of DCR. The clear shock constructions and the physical informations of whole flow field are provide. The results prove that the place of strong shock can effectivily be controlled by means of changeing back pressure. Then the size of recirculating zone in subsonic combustor can be changed and a good condition for organizeing subsonic combustor combustion and a steady flame will be created.