| 一种新型边界层控制技术应用于湍流减阻的实验研究 |
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| 引用本文： | 杨弘炜,高歌.一种新型边界层控制技术应用于湍流减阻的实验研究[J].航空学报,1997,18(4):455-457. |
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| 作者姓名： | 杨弘炜 高歌 |
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| 作者单位： | 北京航空航天大学４０４教研室 |
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| 摘 要： | 对一种新型的边界层控制技术-菱形网圆坑点阵结构的减阻特性进行了研究，水洞实验表明这种结构应用于NACA-16012翼型表面的减阻效果最高可达22%.
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| 关 键 词： | 边界层控制 湍流减阻 水洞实验 |
| 收稿时间： | 1996-09-17; |
EXPERIMENTAL STUDY FOR TURBULENT DRAG REDUCTION USING A NOVEL BOUNDARY CONTROL TECHNIQUE |
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| Yang Hongwei,Gao Ge.EXPERIMENTAL STUDY FOR TURBULENT DRAG REDUCTION USING A NOVEL BOUNDARY CONTROL TECHNIQUE[J].Acta Aeronautica et Astronautica Sinica,1997,18(4):455-457. |
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| Authors: | Yang Hongwei Gao Ge |
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| Institution: | Faculty 404, Beijing University of Aeronautics and Astronautics, Beijing, 100083 |
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| Abstract: | A novel boundary control technique was investigated for its drag reduction abilities, which is a special surface structrure——the concave spherical pits with arranging in the order of a rhombus. The water tunnel experiment indicated that this kind of surface structure on the NACA 16012 foil surface can reduce the flow resistance up to 22%. |
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| Keywords: | boundary layer control turbulent drag reduction water tunnel experiment |
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