Open-type separation on delta wings for leading-edge bluntness

被引:0
作者
Chiba, Kazuhisa [1 ]
Obayash, Shigeru
Nakahashi, Kazuhiro
机构
[1] Tohoku Univ, Dept Aerronaut & Space Engn, Sendai, Miyagi 980, Japan
[2] Tohoku Univ, Inst Fluid Sci, Sendai, Miyagi 980, Japan
关键词
delta wing; leading-edge separation; bluntness effect; open-type separation; SURFACE TRIANGULATION; BOUNDARY-LAYER; VORTEX; COMPUTATIONS; PREDICTION; REFINEMENT; BODY;
D O I
10.2322/tjsass.50.81
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
A numerical simulation was carried out corresponding to recent experiments using delta wings with sharp and blunt leading-edges, which indicates the second primary vortex, at NASA Langley Research Center. However, the experimental data did not reveal the detailed physical phenomena regarding the second primary vortex, because the experiment used only on-the-body-surface data. In the present study, the physical phenomena were revealed using Reynolds-averaged Navier-Stokes computations with three one-equation turbulence models on an unstructured hybrid mesh. The adaptive mesh refinement method in the vicinity of the vortex center was also applied to have more mesh resolution. Consequently, the result quantitatively revealed that appropriate modeling regarding turbulent kinematic viscosity was significant. Moreover, the three-dimensional visualization of the computational fluid dynamics results suggested that the second primary vortex was a developing shear layer merging into an open-type separation generated late by the primary vortex.
引用
收藏
页码:81 / 87
页数:7
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