基于网格/无网格的三维超音速流场数值模拟

蔡晓伟, 谭俊杰, 王园丁, 任登凤

蔡晓伟, 谭俊杰, 王园丁, 任登凤. 基于网格/无网格的三维超音速流场数值模拟[J]. 工程力学, 2014, 31(12): 17-22,39. DOI: 10.6052/j.issn.1000-4750.2013.06.0558
引用本文: 蔡晓伟, 谭俊杰, 王园丁, 任登凤. 基于网格/无网格的三维超音速流场数值模拟[J]. 工程力学, 2014, 31(12): 17-22,39. DOI: 10.6052/j.issn.1000-4750.2013.06.0558
CAI Xiao-wei, TAN Jun-jie, WANG Yuan-ding, REN Deng-feng. NUMERICAL SIMULATION FOR THREE-DIMENSIONAL SUPERSONIC FLOW FIELD BASED ON HYBRID GRID/MESHLESS ALGORITHM[J]. Engineering Mechanics, 2014, 31(12): 17-22,39. DOI: 10.6052/j.issn.1000-4750.2013.06.0558
Citation: CAI Xiao-wei, TAN Jun-jie, WANG Yuan-ding, REN Deng-feng. NUMERICAL SIMULATION FOR THREE-DIMENSIONAL SUPERSONIC FLOW FIELD BASED ON HYBRID GRID/MESHLESS ALGORITHM[J]. Engineering Mechanics, 2014, 31(12): 17-22,39. DOI: 10.6052/j.issn.1000-4750.2013.06.0558

基于网格/无网格的三维超音速流场数值模拟

基金项目: 国家自然科学基金项目(11072114)
详细信息
    作者简介:

    蔡晓伟(1987-), 男, 江苏人, 博士生, 主要从事无网格方法研究(E-mail:davidcaixw@gmail.com); 王园丁(1987-), 男, 江苏人, 博士生, 主要从事大涡模拟研究(E-mail:xiaocai2601@163.com); 任登凤(1979-), 女, 江苏人, 讲师, 硕士, 主要从事计算传热学、工程热物理研究(E-mail:rendengfeng@mail.njust.edu.cn).

    通讯作者:

    谭俊杰(1949-), 男, 湖南人, 教授, 硕士, 博导, 主要从事流体力学计算和实验研究(E-mail:dlxyjx@mail.njust.edu.cn).

  • 中图分类号: O354

NUMERICAL SIMULATION FOR THREE-DIMENSIONAL SUPERSONIC FLOW FIELD BASED ON HYBRID GRID/MESHLESS ALGORITHM

  • 摘要: 该文针对绕三维复杂外形流动的数值模拟,提出了一套基于笛卡尔网格/无网格的混合算法。该算法采用计算效率高的笛卡尔网格覆盖全场,而在计算物体表面及周围邻近区域布置无网格离散点。通过对重叠区域的划分和信息传递,建立各计算区域之间的耦合关系,形成完整的计算系统。为验证混合算法数值模拟的适用性和准确性,该文对超音速圆球绕流进行了计算,将激波的位置、形状与理论分析结果进行了对比。并进一步采用该算法对Ma=2.5、0°~10°攻角下的B1AC2R标准导弹模型进行了计算,获得的气动力系数与实验值基本吻合,表明该文提出的方法可以进行实际工程应用。
    Abstract: To simulate three-dimensional flow around complex geometrics, a hybrid method based on Cartesian grid and meshless method is presented. In this hybrid method, the efficient Cartesian grid covers the whole computational domain, while a relatively small domain adjacent to the body surface is covered by meshless points. By implementing domain identification and information communication in the overlapping domain, several computational domains are coupled together, and the complicated computational system is formed. To validate the applicability and accuracy of this hybrid method, the supersonic sphere flow is calculated, and the location and the shape of the shock obtained are compared with the empirical formula data. The B1AC2R generic missile at Ma=2.5 and angles of attack 0°~10° is also simulated, the computational results including the aerodynamic coefficients are in a good agreement with the experimental data. It is found that the hybrid method presented is available for actual engineering problems.
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出版历程
  • 收稿日期:  2013-06-18
  • 修回日期:  2013-12-08
  • 刊出日期:  2014-12-24

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