凹槽非定常超音速流动的研究  

Research on Unsteady Supersonic Cavity Flow

作　　者：刘欧子[1] 蔡晋生[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力国防科技重点实验室,陕西西安710072

出　　处：《航空计算技术》2011年第4期28-31,共4页Aeronautical Computing Technique

基　　金：国家博士后基金项目资助(20100471635)

摘　　要：用SST的两方程紊流模型,采用时间和空间上二阶的方法,求解雷诺平均N-S方程,得到开放型凹槽的流动特性的变化。数值模拟了飞行马赫数为5时的测试结果,得到不同时刻流场参数的变化。凹槽内流体质量的增加和减少,有助于油气的混合和燃烧,对于维持燃料的超音速燃烧是非常关键的,对超燃冲压发动机燃烧室的设计具有重要的价值。The computational analysis was performed of self- sustained oscillatot3~ flow over the open cavity driven by a shear layer at flight Mach 5.0 condition. By the solution of the Reynolds- averaged NavierStokes equations with a two- equation SST ofturbulence model the unsteady flow was studied. The resonance cycle of the wedge cavity was got by simulation. The amplitude of the pressure oscillation on the aft wall is much higher than that at the other wall due to the mass addition and expulsion mechanism along the aft wall. This periodic mass addition and expulsion could be critical to the fuel and air mixing and flame- holding in the scramjet engine applications.

关 键 词：凹槽 非定常 超音速流动 自激振荡 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]