Control of leading-edge vortices with suction

被引：4
|
作者：
Badran, B [1 ]
McCormick, S [1 ]
Gursul, I [1 ]
机构：
[1] Univ Cincinnati, Dept Mech Ind & Nucl Engn, Cincinnati, OH 45221 USA
来源：
JOURNAL OF AIRCRAFT | 1998年 / 35卷 / 01期
关键词：
D O I：
10.2514/2.2279
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
The feasibility of vortex control by using suction via slit on the upper surface of a delta wing is demonstrated. Flow visualization were carried out in a wind tunnel on both the leading-edge suction and surface suction of two similar model delta wings. The effect of suction has been found more effective in delaying vortex breakdown for suction slits closer to the leading edge. The exact mechanism of how the surface suction affects vortex breakdown is not clear. However, surface suction is less effective than the leading-edge suction.
引用
收藏
页码：163 / 165
页数：3
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