摘要
利用计算流体力学软件Fluent,采用隐式双时间步方法模拟非定常过程,控制方程的离散采用二阶迎风格式,湍流模型选择剪切应力输运(SST)k-ω模型,并求解组分扩散方程,对脉冲式燃烧风洞的起动过程进行了数值模拟,分析了喷管起动时流场结构的变化情况和自由射流区超声速流场的建立过程.计算结果为改进风洞起动特性提供了一定的参考依据.
The starting process of the pulse combustion wind tunnel is unsteady and very complex. It couldn＇t be investigated by use of the experimental method in existence. In this paper, the starting process was simulated by the Fluent computational fluid dynamics（CFD） code. The current version of this code employs dual-time formulation, second order upwind interpolation scheme, shear stress transport （SST） h-ω turbulence model, and species transport equation. The transient flow structure during nozzle starting process and the establishing process of supersonic flow in the free jet region were analyzed. The results provide a reference for the improvement of the starting characteristics of the pulse combustion wind tunnel.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第9期1568-1572,共5页
Journal of Aerospace Power
关键词
脉冲式燃烧风洞
起动过程
数值模拟
喷管
扩压器
pulse combustion wind tunnel
starting process
numerical simulation
nozzle
diffuser
