| 一种改进混合迎风格式在翼型流场激波捕捉中的应用 |
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| 引用本文： | 贾勇,孙刚,刘苏.一种改进混合迎风格式在翼型流场激波捕捉中的应用[J].上海力学,2007,28(2):223-227. |
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| 作者姓名： | 贾勇 孙刚 刘苏 |
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| 作者单位： | 上海交通大学工程力学系 上海200240(贾勇)，复旦大学力学与工程科学系 上海200433(孙刚)，南京军区联勤部 南京221004(刘苏) |
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| 摘 要： | 波阻是飞行器超音速飞行的关键设计因素,精确捕捉激波在流场中的位置,是数值模拟含激波流场和精确计算波阻的一个重要研究内容.本文基于网格节点有限体积空间离散方法,采用AUSM格式与FVS格式的混合格式(MAUSM方法)计算对流通量,从而抑制在数值模拟流场出现的激波处振荡和过冲现象,确保AUSM准确捕获接触间断的特性和FVS格式捕捉激波的能力.本文使用MAUSM方法分别计算了在跨声速和超声速条件下的NACA0012翼型流场,并与中心差分格式的计算结果进行比较.结果表明,对于存在激波的翼型流场,MAUSM方法是有效的.
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| 关 键 词： | MAUSM方法 激波 翼型流场 |
| 文章编号： | 0254-0053（2007）02-223-5 |
| 修稿时间： | 2006-02-06 |
Numerical Simulation of Airfoil Flow with Shock Wave Using Modified AUSM Scheme |
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| JIA Yong,SUN Gang,LIU Su.Numerical Simulation of Airfoil Flow with Shock Wave Using Modified AUSM Scheme[J].Chinese Quarterly Mechanics,2007,28(2):223-227. |
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| Authors: | JIA Yong SUN Gang LIU Su |
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| Institution: | 1. Department of Engineering Mechanics, Shanghai Jiaotong University, Shanghai 200240; 2. Dep. of Mechanics and Engineering Science, Fudan University, Shanghai 200433; 3. Department of Assistant of NanJing Military Command,221004 |
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| Abstract: | Wave drag and the research of numerical precision position of shock wave is a very important factor for the vehicle design in supersonic flow.The modified advection upstream splitting method(MAUSM) is based on finite volume method.The modified advection upstream splitting method is proposed ensuring a sharp and clear resolution of discontinuity.The improved scheme was applied to simulate 2D NACA0012 airfoil flow through several numerical experiments and showed the strong ability to capture shock waves accurately. |
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| Keywords: | MAUSM scheme shock wave airfoil field |
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