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.
出处
《推进技术》
EI
CAS
CSCD
北大核心
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)
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
Supersonic combustion ramjet engine
Turbulent flow
Cavity
Supersonic flow^＋
Numerical simulation
