期刊文献+

动态间断装配法模拟斜激波壁面反射 被引量:9

A moving discontinuity fitting technique to simulate shock waves impinged on a straight wall
原文传递
导出
摘要 基于非结构动网格技术和边界装配思想提出了动态间断装配法,该方法能够应用于求解含有间断的流动问题。无论入射激波还是反射激波都是作为边界进行处理,激波运动速度由兰金-许贡纽(Rankine-Hugoniot)关系确定。激波作为动网格的一部分,其运动由动网格技术实现。采用该方法模拟了超声速二维流场中激波与壁面相交问题,并且与捕捉法进行比较,二者的流场结构符合良好,但是在细节上还是存在明显差异。通过对流动结构的分析,得出采用装配方法得到的流场要优于捕捉方法的结论。激波壁面反射的问题模拟,也说明了边界激波装配方法对于复杂的激波相交问题是具有处理能力的。 A new shock-fitting technique called the moving discontinuity fitting algorithm has been proposed,which is based on the unstructured moving grids technique and boundary shock fitting technique.No matter the incident shock wave or reflected shock wave is treated as a boundary of a flow field,the velocity of shock moving is determined by Rankine-Hugoniot(R-H)relations.The shock wave is fitted as a part of the unstructured moving grids.And the unstructured moving grids technique is used to make the motion of shock waves come true.A problem about shock waves reflection on a straight wall is simulated using this new technique.Compared with the result obtained by shock capturing technique in detail,the result obtained by the new shock fitting is better,though they are similar in general.Using this method,not only incident shock waves but also the reflection shock waves can be fitted.This method shows that the boundary shock fitting technique is also capable of simulating shock interaction even Mach reflection.
出处 《航空学报》 EI CAS CSCD 北大核心 2016年第3期836-846,共11页 Acta Aeronautica et Astronautica Sinica
关键词 激波 非结构动网格 装配法 超声速流动 激波相交 shock wave unstructured moving grids shock fitting supersonic flow shock wave interactions
  • 相关文献

参考文献2

二级参考文献22

  • 1袁先旭,张涵信,谢昱飞,叶友达.非定常数值模拟方法的发展及其在动态绕流中的应用[J].空气动力学学报,2004,22(4):432-437. 被引量:17
  • 2王巍,刘君,郭正.子母弹抛壳过程非定常流动的数值模拟[J].空气动力学学报,2006,24(3):285-288. 被引量:15
  • 3倪云华,杨爱明,翁培奋.低雷诺数下微型飞行器主动变形机翼非定常气动特性数值分析[J].空气动力学学报,2006,24(3):307-313. 被引量:5
  • 4李鹤亭,闫超,龙尧松,等.重叠网格自动生成方法研究[A].第十二届全国计算流体力学会议论文集[C].西安:2004:384-489.
  • 5Thomas P D, Lombard C K. The geometric conservation law- a link between finite- difference and finite- volume methods of flow computation on moving grids[ R]. AIAA 78 -1208, 1978.
  • 6Thomas P D, Lombard C K. Geometric conservation law and its application to flow computations on moving grids [ J ]. AIAA Journal, 1979,17 (10) : 1030 - 1037.
  • 7Lesoinne M, Farhat C. Geometric conservation laws for aeroelastic computations using unstructured dynamic meshes [ R]. AIAA 95 - 1709,1995.
  • 8Koobus B, Farhat C. Second- order implicit schemes that satisfy the GCL for flow computations on dynamic grids [ R]. AIAA 98 - 0113,1998.
  • 9Mabey DG, Welsh BL, Pyne CR. A summary of measurements of steady and oscillatory pressures on a rectangular wing. Aeronautical Journal, 1988, 92(911): 10~28
  • 10Blom FJ. Considerations on the spring analogy. Journal of Aircraft, 2000, 32:647~668

共引文献44

同被引文献24

引证文献9

二级引证文献23

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部