薛大文, 陈志华, 孙晓晖, 陈耀慧. 翼型绕流分离的微楔控制[J]. 工程力学, 2014, 31(8): 217-222. DOI: 10.6052/j.issn.1000-4750.2013.02.0131
引用本文: 薛大文, 陈志华, 孙晓晖, 陈耀慧. 翼型绕流分离的微楔控制[J]. 工程力学, 2014, 31(8): 217-222. DOI: 10.6052/j.issn.1000-4750.2013.02.0131
XUE Da-wen, CHEN Zhi-hua, SUN Xiao-hui, CHEN Yao-hui. MICRO-RAMP CONTROL OF THE BOUNDARY SEPARATION INDUCED BY THE FLOW PAST AN AIRFOIL[J]. Engineering Mechanics, 2014, 31(8): 217-222. DOI: 10.6052/j.issn.1000-4750.2013.02.0131
Citation: XUE Da-wen, CHEN Zhi-hua, SUN Xiao-hui, CHEN Yao-hui. MICRO-RAMP CONTROL OF THE BOUNDARY SEPARATION INDUCED BY THE FLOW PAST AN AIRFOIL[J]. Engineering Mechanics, 2014, 31(8): 217-222. DOI: 10.6052/j.issn.1000-4750.2013.02.0131

翼型绕流分离的微楔控制

MICRO-RAMP CONTROL OF THE BOUNDARY SEPARATION INDUCED BY THE FLOW PAST AN AIRFOIL

  • 摘要: 基于大涡模拟(LES, Large Eddy Simulation),结合3阶WENO(Weighted Essentially Non-Oscillatory)格式与沉浸边界法(IBM, Immersed Boundary Method),对NACA0012翼型在来流马赫数为Ma=0.5以及10°攻角下,有无微型三角楔涡流发生器作用的三维绕流进行了数值模拟,对比了两者的流场结构变化。数值结果表明,微楔能显著改变翼型绕流的尾涡结构,并能缩小其表面边界层的分离,提高升力,并对微型三角楔涡流发生器的流体分离抑制机理进行了讨论。

     

    Abstract: Based on the large eddy simulation (LES) and combined with three-order WENO scheme and the immersed boundary method (IBM), the flows past a NACA0012 airfoil with and without a micro-ramp vortex generator have been simulated at the Mach number of Ma=0.5 and in an angle of attack α=10°, and different flow structures under these two cases have been compared. Our numerical results show that the micro-ramp can change wake structures, and can lead to the reduction of a boundary layer separation area, and an increase of lift. Furthermore, the suppression mechanism of the micro ramp on flow separation have been discussed.

     

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