摘要
网格变形技术被广泛运用于气动外形优化设计或气动弹性力学仿真之中。非结构混合网格由于拓扑结构比较复杂,其网格变形的难度较大。本章发展了一套基于径向基函数的非结构混合网格变形技术。其基本原理是运用径向基函数对物面边界网格节点的位移进行插值,然后利用构造出来的径向基函数插值序列将物面的位移效应光滑地分散到整个网格区域的节点上。为了提高网格变形效率,需要在物面位移的径向基函数插值过程中进行数据精简,为此,文中提出了一种基于贪心法逐级选择径向基函数空间子集来实现插值逼近的数据精简算法。选择NACA0012翼型和三维LANN机翼的非结构混合网格的典型变形问题作为数值算例,对该方法的实用性进行了验证。计算结果表明该方法具备较高的计算效率,对大尺度变形问题的适应性很好,变形后计算网格的质量仍然可以得到有效地保证。
Aim. The introduction of the full paper reviews a number of relevant papers in the open literature and then proposes the deformation technique research mentioned in the title, which we believe is more efficient than previously and which is explained in sections 1 and 2. Their core consists of： ＂In hybrid unstructured grid, mesh deformation becomes difficult due to the complexity of grid topology. In this paper, an efficient mesh deformation technique for hybrid unstructured grid, which is based on radial basis functions, is developed. The principal procedure of this method is divided into two steps. Firstly, a series of radial basis functions is constructed by an interpolation method according to the displacements of moving boundary points. Later, the displacements of all points in the computation domain are determined by the above radial basis function series. In order to improve the efficiency, data reduction should be introduced into the interpolation process. Hence, a multi-level subspace radial basis func- tion interpolation method based on greedy algorithm is presented to create an approximate interpolation instead of the original interpolation which is accurate for all moving boundary points. ＂ Typical deformation problems of NACA0012 airfoil and LANN wing with hybrid unstructured grid are selected as the test cases for demonstration. Calculated results, presented in Figs. 2, 3, 5 and 6 and Tables 1 and 2, and their analysis show preliminarily that the mesh deformation method of this paper has both good efficiency and good robustness on large deformation problems. Another excellent performance of the above method is that the grid quality can be well preserved during the deform- ation process.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2011年第5期783-788,共6页
Journal of Northwestern Polytechnical University
基金
国家自然科学基金(10802067)资助
关键词
径向基函数
非结构混合网格
网格变形
贪心法
aerodynamics, airfoils, algorithms, analysis, approximation theory, calculations, computational complexity, computational geometry, data reduction, interpolation, numerical methods, optimization, topology, wings
greedy algorithm, hybrid unstructured grid, mesh deformation, radial basis function
