摘要
利用可压缩k-ξ模式,对跨声速扩压管内激波/分离可压缩流动流场特性进行数值模拟分析,并将结果与传统涡粘二方程模式k-ω,k-ε模式以及实验值进行比较。k-ξ模式秉承了二方程模式的简单框架,具有良好的数值特性和鲁棒性。为避免由于湍动能奇大而出现的模拟结果偏离实际的现象,可压缩k-ξ模式添加了应力限制器。计算结果表明,修正后的k-ξ新模式在分离区域能较好的模拟流体的流动情况,模拟的速度型与实验值较为接近。尤其是在飞行马赫数为0.9的强激波诱导分离流动流场中,k-ξ模式模拟的扩压管上下壁面压力分布及不同截面速度分布结果更加接近实验值。
Numerical simulation with compressible k-ξ turbulence model was presented,based on the compressible shock wave/separation flow field in Sajben diffuser.The results were compared with the experiment data and numerical results with k-ω and k-ε turbulence model.The k-ξ turbulence model was derived from two-equation eddy viscosity turbulence models,with better numerical characteristics and robustness.A shear stress limiter was incorporated into the model against the unique turbulent kinetic energy.The results show that the new modified k-ξ model can simulate the flow of fluid well in the separation region,and the simulated velocity model is close to the experimental value.Pressure distribution on upper and lower wall and velocity profile on different cross-sections which were numerically simulated by new k-ξ turbulence model,were closer to the experiment data than others,especially in the flow with separation induced by strong shock wave of Mach number 0.9.
作者
高琳
李娜
王广帅
徐月
洪功名
Gao Lin;Li Na;Wang Guangshuai;Xu Yue;Hong Gongming(College of Mechanical Engineering,Xi'an Shiyou University,Xi'an 710065,China;Beijing Electro-mechanical Engineering Institute,Beijing 100074,China;Beijing HIWING Scientific and Technological Information Institute,Beijing 100074,China)
出处
《战术导弹技术》
北大核心
2019年第6期19-25,共7页
Tactical Missile Technology
基金
陕西省教育厅自然科学基金(17JK0615)
关键词
可压缩
激波
涡粘模式
应力限制器
跨声速
扩压管
compressible
shock wave
eddy viscosity turbulence model
shear stress limiter
transonic
diffuser tube
