激波诱导轴对称气动矢量喷管流场数值模拟  

Numerical simulation of flow-field for shock induced axisymmetric fluidic vectoring nozzle

作　　者：雷金春[1] 金捷[1] 

机构地区：[1]北京航空航天大学航空发动机数值仿真研究中心,北京100191

出　　处：《航空动力学报》2008年第9期1585-1590,共6页Journal of Aerospace Power

摘　　要：在落压比3～10，次流相对流量比2．5％～20％工况下，采用RNG k-ε湍流模型对扩张段开缝的激波诱导轴对称气动矢量喷管试验件进行了数值模拟．结果表明：壁面静压分布计算值和试验数据相对误差不大于10．1％．次流的注入使得气动矢量喷管内流流动非常复杂，流场结构的主要特征是在扩张段有一对旋向相反的主分离涡与射流角涡和一个位于次流与出口截面之间较大的回流区．流场结构随着落压比和次流相对流量比的变化而改变．A sub-scaled numerical simulation employing RNG k-ε model was conducted to determine the internal flow-field structure of a shock induced axisymmetric fluidic vectoring nozzle with a slot in its divergent section, when the nozzle pressure ratio （NPR） was 3-10,and the flow flux ratio of the secondary flow injection to the primary flow （Ws/Wp） was 2.5%-20%. The results from comparison of computational and experimental data indicate that, the relative tolerance of wall static distribution is less than 10.1%. The flow-field structure is very complicated for the secondary flow injection. The flow structure is characterized in that, a pair of opposite revolving separated vortex exists in the divergent section and a large recirculation region locates between the secondary flow injection and the outlet. The flow field structure changes with NPR and Ws/Wp.

关 键 词：气动矢量喷管 激波诱导 流场结构 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]