Application of Parallel LES on Airfoil Unsteady Separated Flow at High Reynolds Number and Large Attack Angle
This research is based on NAP A, which is a CFD software developed by Nanjing University of Aeronautics and Astronautics (NUAA). In order to improve this software, techniques of Large Eddy Simulation using a kind of improved Smagorinsky Sub-grid Scale Model and Dual Time-Stepping Method are involved. Parallelization based on MPI library was used to improve the performance. This new improved software was used in the simulation of 2-D circular cylinder flow. Compared with the classical experimental results, the simulation results of this program are satisfactory. Additionally, numerical research on 2-dimensional wing flow with large attack angle was also perfomed, and unsteady eddy structure of this flow was investigated in this paper. Calculating results indicated that the characters of eddies in separated flow and shear flow were revealed correctly.
large eddy simulation cfd parallel computing sub-grid scale model unsteady
Jianfeng Zhu Guoping Huang Yingming Hu Wenyou Qiao
Internal Flow Research Center Nanjing University of Aeronautics and Astronautics Nanjing, P.R.China
国际会议
The 3rd International Symposium on Jet Propulsion and Power Engineering(第三届喷气推进与动力工程国际会议 ISJPPE)
南京
英文
82-88
2010-09-13（万方平台首次上网日期，不代表论文的发表时间）