65°三角翼亚音速复杂流场计算和流动显示
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- 英文论文题名：Numerical Simulation of Complex Subsonic Flow over a 65° Delta Wing
- 论文作者：李立
- 英文论文作者：Li Li ; Aeronautics Computing Technique Research Institute Xi'an
- 年：2016
- 作者机构：中航工业西安航空计算技术研究所;
- 论文关键词：混合网格 ; 有限体积法 ; 旋涡运动 ; VFE-2三角翼 ; 流动显示
- 英文论文关键词：hybrid mesh ; finite volume method ; vortex flow ; VFE-2 delta wing ; flow visualization
- 会议召开时间：2016-10-31
- 会议录名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛文集（下册）
- 英文会议录名称：Discovery,Innovation and Communication——Proceedings of 7th CSAA Science and Technology Youth Forum
- 语种：中文
- 分类号：V211.3
- 学会代码：ZGHU
- 会议名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛
- 会议地点：中国广东中山
- 主办单位：中国航空学会
- 学会名称：中国航空学会
- 页数：6
- 文件大小：1594k
- 原文格式：O
- 会议级别：全国
摘要
提出一种基于非结构混合网格和有限体积法的有效计算策略,成功用于第二届国际涡流试验(VFE-2)尖前缘65°三角翼在马赫数0.4。迎角20.3°,雷诺数2.e+6条件下的亚音速复杂流场的数值模拟,取得了满意的效果。探讨了基于计算数据如何进行该类型复杂涡系干扰表面和空间流场关键特征提取和流动显示方法.为三角翼这类复杂流场结构的精细分析奠定了技术基础,.细致分析了亚音速三角翼的大迎角复杂旋涡流场结均,得到了与试验一致的结论。本文研究进一步证实,在大迎角条件下,三角翼流动物理复杂,黏性效应耦合严重,只有通过N-S方程计算才能准确地捕捉主涡和二次涡的发展。
Numerical investigation on the VFE-2 65° delta wing with sharp leading edge in subsonic at Ma number 0.4,angle of attack 20.3°,and Reynolds number 2.e +6 is performed by using an unstructured hybrid mesh based finite volume method,with which emphasis is to have discussions on how to extract the key flow features for visualization both on surface and in space for such type complex flow.Approaches both for qualitative analysis and quantitative analysis have been established,which have laid a solid foundation for elaborated analysis for complex flow structures of delta wing.With these approaches,the complex vortex flow structure of the subsonic delta wing at high angle of attack has been analysis,and compatible findings to experiments have been obtained.It is illustrated in this paper that flow over delta wing at high angle of attack has a complex physics with strong viscous coupling effect,and the evolutions of the primary and secondary vortex can be accurately captured only by an N-S equation based simulation.
Numerical investigation on the VFE-2 65° delta wing with sharp leading edge in subsonic at Ma number 0.4,angle of attack 20.3°,and Reynolds number 2.e +6 is performed by using an unstructured hybrid mesh based finite volume method,with which emphasis is to have discussions on how to extract the key flow features for visualization both on surface and in space for such type complex flow.Approaches both for qualitative analysis and quantitative analysis have been established,which have laid a solid foundation for elaborated analysis for complex flow structures of delta wing.With these approaches,the complex vortex flow structure of the subsonic delta wing at high angle of attack has been analysis,and compatible findings to experiments have been obtained.It is illustrated in this paper that flow over delta wing at high angle of attack has a complex physics with strong viscous coupling effect,and the evolutions of the primary and secondary vortex can be accurately captured only by an N-S equation based simulation.
引文
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[2]Konralh R,Klein C,Schroder A.PSP and PIV Investigations on the VFE-2 Configuration in Sub-and Transonic Flow[C].46th AIAA Aerospace Sciences Meeting and Exhibit 7-10 January 2008,Reno,Nevada(AIAA 2008-379).
[3]阎超,于剑,徐晶磊,等.CFD模拟方法的发展成就与展望[J].力学进展,2011,41(5):562-588.
[4]Jameson A,Schmidt W,Turkel E.Numerical Solutions of the Euler Equations by Finite Volume Methods Using Runge_Kutta Time Stepping Scheme[R].AIAA,81-1259,1981.
[5]朱培烨.三维非结构网格的欧拉方程聚合多重网格法[J].航空计算技术,2004,34(3):6-9.
[6]Chu J,and Luckring J M.Experimental Surface Pressure Data obtained on 65°Delta Wing Across Reynolds Number and Mach Number Ranges[R],NASA Technical Memorandum 4645,1996.
[7]Fritz W.What Was Learned From the Numerical Simulations for the VFE-2[R].AIAA,2008-399,2008.
[8]Bai Wen,Qiu Zheng,Li Li.Recent Efforts to Establish Adaptive Hybrid Grid Computing Capability at ACTRI[J].Computational Fluid Dynamics Journal,15(4):438-449.
[9]李立,白文,梁益华.基于伴随方程方法的非结构网格自适应技术及应用[J].空气动力学报,2011,29(3):309-316.
[10]Pirzadeh S Z.Vortical Flow Predication Using an Adaptive Unstructured Grid Method.RAT AVT Symposium on Advanced Flow Management:Part AVortex Flows and High Angle of Attack for Military Vehicles,Norway;Loen,May 2001.
[2]Konralh R,Klein C,Schroder A.PSP and PIV Investigations on the VFE-2 Configuration in Sub-and Transonic Flow[C].46th AIAA Aerospace Sciences Meeting and Exhibit 7-10 January 2008,Reno,Nevada(AIAA 2008-379).
[3]阎超,于剑,徐晶磊,等.CFD模拟方法的发展成就与展望[J].力学进展,2011,41(5):562-588.
[4]Jameson A,Schmidt W,Turkel E.Numerical Solutions of the Euler Equations by Finite Volume Methods Using Runge_Kutta Time Stepping Scheme[R].AIAA,81-1259,1981.
[5]朱培烨.三维非结构网格的欧拉方程聚合多重网格法[J].航空计算技术,2004,34(3):6-9.
[6]Chu J,and Luckring J M.Experimental Surface Pressure Data obtained on 65°Delta Wing Across Reynolds Number and Mach Number Ranges[R],NASA Technical Memorandum 4645,1996.
[7]Fritz W.What Was Learned From the Numerical Simulations for the VFE-2[R].AIAA,2008-399,2008.
[8]Bai Wen,Qiu Zheng,Li Li.Recent Efforts to Establish Adaptive Hybrid Grid Computing Capability at ACTRI[J].Computational Fluid Dynamics Journal,15(4):438-449.
[9]李立,白文,梁益华.基于伴随方程方法的非结构网格自适应技术及应用[J].空气动力学报,2011,29(3):309-316.
[10]Pirzadeh S Z.Vortical Flow Predication Using an Adaptive Unstructured Grid Method.RAT AVT Symposium on Advanced Flow Management:Part AVortex Flows and High Angle of Attack for Military Vehicles,Norway;Loen,May 2001.