To help carry out the numerical analysis of micro vortex generator (VG)used to control the flow separation of a high lift system, several crucial issues that occur during numerical simulation are solved in this paper. First, in order to avoid excessive grid number caused by the conventional point-to-point gird method, a patched grid technique is adopted. Second, a special boundary condition definition method is used to correspond respectively to the cases of the fitting and non-fitting of micro vortex generator, which will eliminate the disturbance caused by grid change. The combination of such two methods generates a new approach for the numerical analysis of a high lift system with micro vortex generator on it. The wind tunnel data prove that this approach achieves good numerical accuracy and can meet the needs of related research. It offers a reliable way during the numerical research of micro vortex generator design and parameter optimization.
CHU Hubing, CHEN Yingchun, ZHANG Binqian, LI Yanlin
. Investigation of Numerical Simulation Technique for Micro Vortex Generators Applied to High Lift System[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012
, 33(1)
: 11
-21
.
DOI: CNKI:11-1929/V.20110712.0904.002
[1] Meredit H P. Viscous phenomena affecting high lift systems and suggestions for future CFD development. AGARD CP-515, 1993.
[2] Gamer P L, Meredith P T, Stoner R C. Areas for future CFD development as illustrated by transport aircraft applications. AIAA-1991-1527, 1991.
[3] Lin J C, Robinson S K. Separation control on high-lift airfoils via micro-vortex generators. AIAA-1994-46653, 1994.
[4] Bohannon K S. Passive flow control on civil aircraft flaps using sub-boundary layer vortex generators in the AWIATOR programme. AIAA-2006-2858, 2006.
[5] Brunet V, Francois C. Experimental and numerical investigations of vortex generators effects. AIAA-2006-3027, 2006.
[6] Meunier M, Brunet V. High-lift devices performance enhancement using mechanical and air-jet vortex generators. AIAA-2008-36836, 2008.
[7] Huang J B, Xiao Z X, Fu S, et al. Study of control effects of vortex generators on a supercritical wing. Science China Technological Sciences, 2010, 40 (8): 867-878. (in Chinese). 黄静波, 肖志祥, 符松, 等. 超临界机翼表面涡流发生器影响研究[J]. 中国科学: 技术科学, 2010, 40 (8): 867-878.
[8] Liu G, Liu W, Mou B, et al. CFD numerical simulation investigation of vortex generators. Acta Aerodynamica Sinica, 2007, 25(2): 241-244. (in Chinese) 刘刚, 刘伟, 牟斌, 等. 涡流发生器数值计算方法研究. 空气动力学学报, 2007, 25(2): 241-244.
[9] von Stillfield F, Wallin S. Application of a statistical vortex generator model approach on the short-chord flap of a three-element airfoil. GRDI-2000-25205, 2000.
[10] Godard G, Stanislas M. Control of a decelerating boundary layer. Part 1: Optimization of passive vortex generator. Aerospace Science and Technology, 2006, 10: 181-191.
[11] Edwards J B W. Free-flight tests of vortex generator configurations at transonic speeds. Ministry of Aviation, C. P. No. 729, 1966.
[12] Zhang J, Zhang B Q. Investigation of boundary layer separation control for supercritical airfoil using micro vortex generator. Journal of Experiments in Fluid Mechanics, 2005, 19(3): 58-61. (in Chinese) 张进, 张彬乾. 控制超临界翼型附面层分离的微型涡流发生器研究. 实验流体力学, 2005, 19(3): 58-61.
[13] Sang W M, Li F W. Numerical analysis of flows around 3D high lift system by adaptive Cartesian grid method. Acta Mechanica Sinica, 2005, 37(1): 80-86. (in Chinese) 桑为民, 李凤蔚. 采用自适应直角网格计算三维增升装置绕流. 力学学报, 2005, 37(1): 80-86.
[14] Shi Y B, Wang H J, Li J. Exploring a feasible method of CFD simulation of high-lift aircraft configuration using patched-grid generation method and multi-grid technique. Journal of Northwestern Polytechnical University, 2010, 28(1): 143-146. (in Chinese) 石永彬, 王豪杰, 李杰. 基于面搭接多重网格技术的全机增升装置绕流数值模拟. 西北工业大学学报, 2010, 28(1): 143-146.
[15] Li S F. Navier-Stokes simulations for complex high lift configuration by using patched-grid technique. Xi'an: School of Aeronautics, Northwestern Polytechnical University, 2008. (in Chinese) 李少飞. 基于面搭接多块网格技术的复杂流场N-S方程数值模拟研究. 西安: 西北工业大学航空学院, 2008.
[16] Johnson P L, Jones K M. Experimental Investigation of a simplified 3d high lift configuration in support of CFD validation. AIAA-2000-4217, 2000.
[17] Rumsey C L, Ying S X. Prediction of high lift: review of present CFD capability. Aerospace Sciences, 2002, 38: 145-180.
[18] Chan M S, Pirzadeh S. Unstructured Navier-Stokes high-lift computations on a trapezoidal wing. AIAA-2005-5084, 2005.