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多段翼型大迎角分离流动的DELAYED RANS/LES混合算法 被引量：4

DELAYED RANS/LES Method For High Attack Angle Flow over Multi-element Airfoil
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摘要 多段翼型的大迎角绕流发生大范围附面层分离,具有明显的三维与非定常流动特性。RANS/LES混合算法继承了LES对流动分离区大尺度漩涡准确模拟的优点,避免了纯LES算法需求网格量巨大与亚格子模型壁面函数不成熟等问题,对分离流动的模拟效果优于RANS算法。以S-A湍流模型与Smagorinsky亚格子模型为基础,借鉴DDES的附面层延迟控制思想,构造了可用于对接网格、重叠网格的DELAYED RANS/LES混合算法。研究了GA(W)-1多段翼型的大迎角分离流动及其气动特性。 The massively separated flows over multi- element airfoil are three- dimensional and time- dependent. RANS/LES Hybrid method combines the power of RANS in the attached boundary layers with the power of LES in separated flow regions. Hybrid Method computation of massively separated flows is superior to RANS. In this paper, an improved Hybrid Method based on S- A turbulence model and Smagorinsky SGS model, DELAYED RANS/LES is implemented on both point- to- point multiblock grid and overset grid. With these methods, the massively separated flows over multi- element airfoil is numerically simulated and analysed.
作者 宋科 乔志德
机构地区 西北工业大学翼型叶栅国防科技重点实验室
出处 《航空计算技术》 2009年第3期42-47,55,共7页 Aeronautical Computing Technique
关键词 DELAYED RANS/LES混合算法 Smagorinsky模型 多段翼型 大迎角 分离流动 DELAYED RANS/LES multi- element airfoil hight attack angle separated flows
分类号 V211 [航空宇航科学与技术—航空宇航推进理论与工程]
  • 相关文献

参考文献18

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共引文献22

同被引文献39

  • 1高慧,傅德薰,马延文,李新亮.Direct Numerical Simulation of Supersonic Turbulent Boundary Layer Flow[J].Chinese Physics Letters,2005,22(7):1709-1712. 被引量：8
  • 2朱自强,陈迎春,吴宗成,陈泽民.高升力系统外形的数值模拟计算[J].航空学报,2005,26(3):257-262. 被引量：48
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引证文献4

二级引证文献10

航空计算技术
2009年 第3期

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