复杂外形网格生成技术及应用

张正科; 朱自强; 庄逢甘

复杂外形网格生成技术及应用

1.
北京航空航天大学宇航学院
2. 北京航空航天大学飞行器设计与应用力学系

基金项目: 国家自然科学基金(19502002)和博士后科学基金资助项目

详细信息

中图分类号: V 211.3
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- 文章访问数: 3144
- HTML全文浏览量: 284
- PDF下载量: 1275
- 被引次数: 0
出版历程
- 收稿日期: 1998-05-18
- 网络出版日期: 1998-06-30

Grid Generation Technique of Complex Configurations and its Applications

1.
Beijing University of Aeronautics and Astronautics,Dept.of Flight Vehicle Design and Applied Mechanics
2. Beijing University of Aeronautics and Astronautics,Dept.of Flight Vehicle Design and Applied Mechanics

摘要

摘要: 以某型双立尾战斗机为例,给出了实际复杂型号飞行器结构网格生成的一种分块方案及实现过程,用一种矢性三次多项式插值的方法生成相邻块公共交界面的网格,用Hilgenstock方法修正源项,求解椭圆型方程生成块内空间网格,使网格线与边界面夹角、与边界面间距控制为期望的值.在所生成的双立尾战斗机分块结构网格中求解Euler方程,获得了合理的全机气动力系数、翼面压力分布和绕流图谱结果.
- 网格 /
- 战斗机 /
- 计算流体力学 /
- 分块网格 /
- Euler方程
Abstract: A multiblock structured grid generation system for complex practical aircraft is presented and applied in the grid generation of a twin-tail fighter. A vectorized polynomial of degree 3 is used to generate grid on the interface of adjacent blocks. The volume grid in each block is generated by solving elliptic partial differential equations with source terms corrected by 3-d Hilgenstock method to control the grid line angle (orthogonality) to boundaries and first-layer grid point spacings off boundaries to expected values. Euler equations are solved in the generated grid of the twin-tail fighter and the computed results of the aerodynamic coefficients of the complete aircraft, the wing surface pressure and the vortical flow field are reasonable.
- grids /
- fighter /
- computational fluid mechanics /
- multiblock grid /
- Euler equations

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参考文献(1)

1. Thompson J F,Weatherill N P.Aspects of numerical grid generation:current science and art. AIAA 93-3539-CP,1993 2. Pearce D G,Stanley S A,Martin Jr F W,et al.Development of large scale chimera grid system for the space shuttle launch vehicle. AIAA 93-0533,1993 3. Dominik D,Wisneski J,Rajagopal K,et al.Grid generation of a high fidelity complex multibody space shuttle mated vehicle. AIAA 93-0432,1993 4. Sonar T. Grid generation using elliptic partial differential equations. Braunschweig:Deutsche Forschungs-und Versuchsanstalt für Luft-und Raumfahrt, 1989.1~122 5. Thompson J F, Thames F C,Mastin C W. Automatic numerical generation of body-fitted curvilinear coordinates for a field containing any number of arbitrary two-dimensional bodies. J of Computational physics, 1974,15(3):299~319 6. Thomas P D. Composite three-dimensional grids generated by elliptic system. AIAA J, 1982,20(9):1195~1202 7. Steger J L,Sorenson R L. Automatic mesh-point clustering near a boundary in grid generation.J of Computational physics, 1979,33(3):405~410 8. White J A. Elliptic grid generation with orthogonality and spacing control on an arbitrary number of boundaries. AIAA90-1568,1990 9. 张正科.翼身组合体跨音速大迎角欧拉方程多重网格数值解:[学位论文].西安:西北工业大学飞机系,1994[ZK)] 10. [ZK(#]张正科,庄逢甘,朱自强.两种椭圆型方程求源项方法在喷管内流场网格生成中的应用.推进技术,1997,18(2):95~97 11. 张正科,李凤蔚,罗时钧.用椭圆型方程生成三维贴体与边界正交网格.西北工业大学学报,1995,13(1):143~146 12. 张正科,朱自强,庄逢甘,罗时钧.三维椭圆型方程网格生成中的新源项修正法.北京航空航天大学学报,1997,23(4):452~455 13. 张正科.多部件复杂飞行器分块网格生成及其大迎角绕流场Euler方程分区解.博士后研究工作报告,北京航空航天大学飞行器设计与应用力学系,1996 14. 蔡晋生,李凤蔚,罗时钧.跨音速大迎角Euler方程数值分析.航空学报A辑,1993,14(5):235~240 15. Verhaagen N G, Jenkins L N, Kern S B,et al.A study of the vortex flow over a 76/40-deg double-delta wing. AIAA 95-0650,1995

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