基于RSM模型的管内正激波/附面层干扰数值分析  

Numerical analysis of normal shock wave/boundary-layer interactions by using RSM

作　　者：田旭昂[1] 王成鹏[1] 程克明[1] 

机构地区：[1]南京航空航天大学空气动力学系,江苏南京210016

出　　处：《空气动力学学报》2013年第2期156-162,共7页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(10702029)

摘　　要：使用RSM湍流模型对来流Ma=1.68矩形等截面管道内的正激波/附面层干扰流动进行了三维数值模拟,将计算结果与实验数据和k-ωSST模型计算结果进行了分析比较。结果表明,由于考虑了流动各向异性,RSM模型计算结果能够捕捉到流场横截面中的二次旋涡流动,相对k-ωSST模型更为准确地模拟了壁面及角流区附面层流动形态和分离特性,与实验数据吻合的更好。分析激波串第一道"λ"激波在壁面角流区的激波分叉结构发现,激波串在壁面的作用下,在管道内的上下壁和侧壁附近都会发生激波分叉现象形成三维"λ"激波;其中第一道"λ"激波的前腿激波会在近壁处二次发生激波/附面层干扰作用,形成范围较小的新的"λ"分叉激波。The three-dimensional flow structure induced by normal shock wave/turbulent boundary-layer interaction in a constant-area rectangular duct at Ma= 1.68 is numerically investigated by using the Reynolds Stress Model and κ-ω SST turbulent model. In comparison with SST model, the RSM model resolves second- ary flow effects, and therefore a reduced corner separation zone is acquired. This leads to a better match be- tween the experimental data and the RSM results. Under the effect of the wall friction due to viscosity, the shocks of shock train will bifurcate near both top/bottom walls and side walls, and the three-dimensional ＂λ＂ shock waves are formed at the duct corner. In the position close to the wall, the foreleg shock of the first ＂λ＂ shock splits and a new smaller ＂λ＂ shock wave is observed.

关 键 词：激波 附面层干扰 RSM模型 激波串 伪激波 “λ”激波 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] O357.42[理学—流体力学]