| 一种通量加权型紧致格式 |
| |
| 引用本文： | 袁湘江,涂国华,许坦,陆利蓬.一种通量加权型紧致格式[J].航空动力学报,2008,23(1):64-69. |
| |
| 作者姓名： | 袁湘江 涂国华 许坦 陆利蓬 |
| |
| 作者单位： | 1.中国空气动力研究与发展中心, 绵阳 621000 |
| |
| 基金项目： | 国家自然科学基金(1032100210672012) |
| |
| 摘 要： | 将通量加权的思想引入到紧致格式中,构造了一个传统方法与紧致格式混合组成的加权型差分格式.利用该格式与二阶TVD格式分别计算了一维方波、组合波问题和一些黎曼问题,如Sod问题和Shu问题,以及一维定常激波问题.计算结果的比较表明加权格式无论在捕捉各种间断,还是在分辨各种复杂波系上,都具有较大的优势,并与精确解非常吻合.
|
| 关 键 词： | 航空、航天推进系统 数值方法 迎风紧致格式 通量加权型差分格式 |
| 文章编号： | 1000-8255(2008)01-0064-06 |
| 收稿时间： | 2006/12/27 0:00:00 |
| 修稿时间： | 2006年12月27 |
A flux-weighted compact scheme |
| |
| YUAN Xiang-jiang,TU Guo-hu,XU Tan and LU Li-peng.A flux-weighted compact scheme[J].Journal of Aerospace Power,2008,23(1):64-69. |
| |
| Authors: | YUAN Xiang-jiang TU Guo-hu XU Tan and LU Li-peng |
| |
| Institution: | 1.China Aerodynamics Research and Development Center, Mianyang 621000, China2.National Computational Fluid Dynamics Laboratory, Beijing University of Aeronautics and Astronautics, Beijing 100083, China3.School of Aeronautics Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China4.School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China |
| |
| Abstract: | With introduction of flux-weighted concept into the compact scheme,a new flux-weighted compact scheme was presented by combining classical scheme and compact scheme.This scheme and a 2nd-order total variation diminishing(TVD) scheme were used to calculate one-dimensional square waves,combine waves and some Riemann problems,such as Sod problem and Shu problem,as well as one-dimensional steady shock.The results show that the new scheme has advantage over the 2nd-order TVD scheme in capturing various discontinuities or resolving various complex waves.The results solved by the new scheme are also highly consistent with exact solutions. |
| |
| Keywords: | aerospace propulsion system numerical method upwind compact scheme weighted essentially non-oscillatory(WENO) schemess |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
| 点击此处可从《航空动力学报》下载免费的PDF全文 |
|
