空气动力学学报2013，Vol.31Issue(2)：156-162,7.
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
摘要
Abstract
The three-dimensional flow structure induced by normal shock wave/turbulent boundary-layer interaction in a constant-area rectangular duct at Ma = l. 68 is numerically investigated by using the Reynolds Stress Model and k-ω SST turbulent model. In comparison with SST model, the RSM model resolves secondary flow effects, and therefore a reduced corner separation zone is acquired. This leads to a better match between 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Key words
shock wave/boundary-layer interaction/ RSM/ shock train/ pseudo shock wave/ "λ" bifurcated shock wave分类
航空航天引用本文复制引用
田旭昂,王成鹏,程克明..基于RSM模型的管内正激波/附面层干扰数值分析[J].空气动力学学报,2013,31(2):156-162,7.基金项目
国家自然科学基金(10702029) （10702029）
