基于混合笛卡儿网格方法的可压流动数值模拟

沈志伟; 赵宁; 胡偶

doi:10.13224/j.cnki.jasp.2015.03.001

基于混合笛卡儿网格方法的可压流动数值模拟

doi: 10.13224/j.cnki.jasp.2015.03.001

南京航空航天大学航空宇航学院, 南京 210016

基金项目:

国家自然科学基金(11002071,11102179)

详细信息

作者简介:
沈志伟(1988-),男,江苏靖江人,博士生,主要从事计算流体力学中混合网格方法的研究.

中图分类号: V211
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出版历程
- 收稿日期: 2013-10-16
- 刊出日期: 2015-03-28

Numerical simulation of compressible flows based on hybrid Cartesian grid method

College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 以可压缩黏性流动的数值模拟为研究背景,发展了一套自适应混合笛卡儿网格(AHCG)方法以及基于有限体积方法的雷诺数平均Navier-Stokes(RANS)的数值求解方法.为更好地模拟边界层的黏性流动在近壁面处采用贴体结构网格,剩余计算区域自动生成与之相重叠的笛卡儿网格,并同时发展了基于流场特征的笛卡儿网格自适应技术.结合ADT(alternating digital tree)算法显著减少了网格生成中“挖洞”和“贡献单元”搜索的消耗机时,50万左右的网格数目下,搜索耗时为0.062s,仅为普通遍历方法的1/1847.通过二维圆柱与两段翼型绕流的数值算例显示,定常AHCG方法能够准确地预测物面压力分布与升阻力系数并且具备处理复杂外形的能力;同时通过二维非定常圆柱绕流问题与NACA0015矩形机翼翼尖尾涡的捕捉算例显示,结合了动态自适应网格加密的非定常AHCG方法尤其适用于旋涡主导流动.
- 混合笛卡儿网格 /
- 雷诺数平均Navier-Stokes /
- 自适应网格加密 /
- ADT算法 /
- 复杂外形
Abstract: An adaptive hybrid Cartesian grid (AHCG) method with a finite volume type Reynolds average Navier-Stokes (RANS) flow solver was developed for simulation of compressible viscous flows. While the near body region was provided with body-fitted structured grids to resolve the boundary layers, the remaining computational domain was tessellated with generated Cartesian grid, and feature-based grid adaptations were carried out for simulating the flowfield more accurately. By using the ADT (alternating digital tree) algorithm, the costed turnaround time of chimera type hole-cutting and identification of donor cells could be decreased very efficiently, and 0.062s was costed, up to only 1/1847 of the normal traversal approach when the grid number reached 500000. Through simulations of flow past 2-D cylinder and 2-element airfoil, it is concluded that steady AHCG method can predict surface pressure distribution, lift and drag coefficients successfully and has the ability of solving complex configurations. The simulation of unsteady flow past 2-D cylinder and the capture of 3-D wing tip vortex past a NACA0015 rectangular wing demonstrates that unsteady AHCG method with dynamic adaptive mesh refinement is especially suited for vortex-dominated flows.
- hybrid Cartesian grid /
- Reynolds average Navier-Stokes /
- adaptive mesh refinement /
- alternating digital tree algorithm /
- complex configurations

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参考文献(24)

[1]	Anderson W K.A grid generation and flow solution method for the Euler equations on unstructured grids[J].Journal of Computational Physics,1994,110(1):23-28.
[2]	阎超.计算流体力学方法及应用[M].北京:北京航空航天大学出版社,2006.
[3]	Marcum D.Generation of unstructured grids for viscous flow applications[R].AIAA 95-0212,1995.
[4]	Coirier W J,Powell K G.An accuracy assessment of Cartesian mesh approaches for the Euler equations[J].Journal of Computational Physics,1995,117(1):121-131.
[5]	Domel N D,Karmen S L.Splitflow:progress in 3D CFD with Cartesian Omni-tree grids for complex geometries[R].AIAA-2000-1006,2000.
[6]	Aftosmis M J,Berger M J,Melton J E.Robust and efficient Cartesian mesh generation for component-based geometry[R].AIAA 97-0196,1997.
[7]	Steger J L,Dougherty F C,Benek J A.A chimera grid scheme[R].Houston,TX:ASME Mini-Symposium on Advances in Grid Generatioan,1982.
[8]	Chiu I T,Meakin R L.On automationg domain connectivity for overset grids[R].AIAA 95-0854,1995.
[9]	Bonet J,Peraire J.An alternating digital tree (ADT) algorithm for 3D geometric searching and intersection problems[J].International Journal for Numerical Methods in Engineering,1991,31(1):1-17.
[10]	Benek J A,Steger J I.Chimera:a grid-embedding technique[R].AEDC-TR-85-64,1985.
[11]	Munikrishna N,Liou M S.A Cartesian based body-fitted adaptive grid method for compressible viscous flows[R].AIAA-2009-1500,2009.
[12]	Cho K W,Kwon J H.Development of a fully systemized chimera methodology for steady/unsteady problems[J].Journal of Aircraft,1999,36(6):973-980.
[13]	Blazek J.Computational fluid dynamics:principles and applications[M].Amsterdam:Elsevier,2001.
[14]	Sharov D,Nakahashi K.Reordering of 3-D hybrid unstructured grids for vectorized LU-SGS Navier-Stokes calculations[R].AIAA 97-2102,1997.
[15]	Liou U M S.A sequel to AUSM:AUSM+[J].Journal of Computational Physics,1996,129(2):364-382.
[16]	Venkatakrishnan V.On the accuracy of limiters and convergence to steady state solutions[R].AIAA 93-0880,1993.
[17]	Menter F R.Two-equation eddy-viscosity turbulence models for engineering applications[J].AIAA Journal,1994,32(8):1598-1605.
[18]	Zeeuw D L.A quadtree-based adaptively-refined Cartesian-grid algorithm for solution of the Euler equations[D].Michigan:University of Michigan,1993.
[19]	Kamkar S J,Wissink A M,Sankaran V,et al.Feature-driven Cartesian adaptive mesh refinement for vortex-dominated flows[J].Journal of Computational Physics,2011,230(16):6271-6298.
[20]	Bashkin V A,Vaganov A V,Egorov I V,et al.Comparison of calculated and experimental data on supersonic flow past a circular cylinder[J].Fluid Dynamic,2002,37(3):473-483.
[21]	Van D V.Boundary layer measurements on a two-dimensional wing with flap[R].New Left Review TR79009U,1979.
[22]	王运涛,孟德虹,邓小刚.多段翼型高精度数值模拟技术研究[J].空气动力学学报,2013,31(1):88-93. WANG Yuntao,MENG Dehong,DENG Xiaogang.High-order numerical study of complex flow over multi-airfoil[J].Acta Aerodynamica Sinica,2013,31(1):88-93.(in Chinese)
[23]	Bake W K.Dipolesound from cylinders mechanics of flow-induced sound and vibration[M].New York:Academic Press,1996.
[24]	Mcalister K W,Takahashi R K.NACA0015 wing pressure and trailing vortex measurements[R].NASA TP3151,1991.