Dynamics of Vortical Flows Induced by Swept-Notched Wings in Aircraft Wake Simulations

L. Szkatula; R. J. Grant; Z. Zouaoui

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Dynamics of Vortical Flows Induced by Swept-Notched Wings in Aircraft Wake Simulations

机译：飞机尾迹仿真中由后掠式机翼引起的涡流动力学

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The motivation behind the present investigations is the alleviation of vortex wake hazard. The influence of wing-tip geometry modifications on the near-field wake behind swept-notched wings is investigated up to 24 span lengths, using computational fluid

机译：本研究背后的动机是减轻涡流尾流危害。使用计算流体，研究了翼尖几何形状修改对扫掠后的机翼后面的近场尾流的影响，其范围长达24个

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来源
《Journal of Aircraft》 |2008年第2期|p.448-460|共13页
作者
L. Szkatula; R. J. Grant; Z. Zouaoui;
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作者单位

University of Wales, Wrexham, LL11 2 AW, United Kingdom;

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收录信息美国《科学引文索引》(SCI);美国《工程索引》(EI);
原文格式 PDF
正文语种 eng
中图分类航空;
关键词
c: = wing chord; b_(TF): = tip-flap vortex separation distance; C_L: = lift coefficient; C_M: = induced rolling moment coefficient; C_M~*: = maximum induced rolling moment coefficient; dA: = cross-sectional area; k: = turbulent kinetic energy; Re: = chor;

机译：c：=翼弦;b_（TF）：=皮瓣涡流分离距离;C_L：=升力系数;C_M：=感应侧倾力矩系数;C_M〜*：=最大感应侧倾力矩系数;dA：=横截面面积;k：湍动能;Re：=脉动;

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Dynamics of Vortical Flows Induced by Swept-Notched Wings in Aircraft Wake Simulations

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