可压缩湍流边界层近壁区马蹄涡的演化  

The evolution of the horseshoe-shaped vortex in the near-wall region of compressible turbulent boundary layer

作　　者：史万里[1] 葛宁[1] 陈林[2] 唐登斌[2] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]南京航空航天大学航空宇航学院,江苏南京210016

出　　处：《空气动力学学报》2011年第6期751-758,共8页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(10772082)

摘　　要：采用大涡模拟方法对可压缩槽道湍流进行了数值模拟。通过给定扰动波方法确定进口边界条件,很快得到了完全发展的湍流。利用动态亚格子模型、预处理技术以及高阶格式和方法,得到了精确的数值结果。计算得到的速度剖面和脉动分量与直接数值模拟的解进行了对比,验证了计算结果的可靠性。结果清楚地展示了湍流场中马蹄涡的生成和演化过程,包括对称涡腿、单侧涡腿的马蹄涡结构,以及流场中存在由亚谐波引起的拟序结构的交错现象。分析了湍流边界层近壁区可能出现的复杂的马蹄涡结构,及其涡结构形状也不严格对称的现象。The full developed turbulent flow in channels was simulated using Large Eddy Simulation （LES） with a given disturbance wave in inlet boundary, after a short development section. The dynamic subgrid-scale model, the preconditioned algorithm and high-order scheme are used in computing. The numerical results are precise. The computed results showed good agreement with DNS, which included root mean square fluctuated velocity distribution and average velocity distribution. This shows the reliability of simulation. The results clearly show the formation and evolu- tion of the horseshoe vortex in the turbulent flow, including the symmetric vortex legs of horseshoe vortex structure and one-side leg of horseshoe vortex, and the staggered phenomenon of the coherent structures caused by subharmonic. Based on this, the complex horseshoe vortex structure in the turbulent boundary layer is analyzed. It is found that the vortex structure of is not strictly symmetrical shape.

关 键 词：大涡模拟 马蹄涡 拟序结构 湍流边界层 动态亚格子模型 

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]