二维凹腔超声速流动的混合RANS/LES模拟  

Hybrid RANS / LES simulation of the supersonic flow over two-dimensional cavities

作　　者：孙明波[1] 梁剑寒[1] 王振国[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2006年第2期119-123,共5页Journal of Propulsion Technology

基　　金：国防科技预研基金(51413040901KG0145)

摘　　要：基于M enter的k-ωSST湍流模型构建了一种混合RANS/LES模拟方法,通过采用一个与到壁面距离相关的衔接函数将处理近壁区的SST模型过渡到处理主流区的Yosh izawa一方程亚格子模型。利用此方法对用于超燃冲压发动机的凹腔的二维超声速流动进行模拟,模拟结果再现了二维凹腔剪切层的拟序结构,计算得到的凹腔自激振荡频率、时均统计的压力分布以及压力剖面与实验结果吻合较好。A hybrid RANS（ Reynolds-Averaged Navier-Stokes）/LES（ Large Eddy Simulation） approach based on Menter＇ s k-ω SST model was developed, using a distance-dependent blending function to shift the turbulence closure from SST model near solid surfaces to a Yoshizawa one-equation subgrid closure in free shear layer regions. The hybrid methodology was conducted to investigate the supersonic flow over two-dimensional open cavities for scramjet applications, Coherent structures of cavity flowfields are revealed by calculation. Numerical results agree well with the experimental data for dominant frequencies and time-averaged surface pressure profiles inside the cavity.

关 键 词：超音速冲压喷气发动机 湍流 凹腔 超声速流动^+ 数值仿真 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]