Low-Reynolds-Number Flowfield of Wing with Control Surface in Propeller Slipstream

被引：6
|
作者：
Ikami, Tsubasa [1 ]
Fujita, Koji [2 ]
Nagai, Hiroki [2 ]
机构：
[1] Tohoku Univ, Inst Fluid Sci, Grad Sch Aerosp Engn, Dept Aerosp Engn, Sendai, Miyagi 9808577, Japan
[2] Tohoku Univ, Inst Fluid Sci, Sendai, Miyagi 9808577, Japan
来源：
JOURNAL OF AIRCRAFT | 2021年 / 58卷 / 02期
基金：
日本学术振兴会;
关键词：
BOUNDARY-LAYER; TRANSITION; AIRFOIL; FLOW; WAKE;
D O I：
10.2514/1.C035880
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
An experimental study is conducted on a NACA 0012 airfoil with a control surface to investigate the influence of a propeller slipstream under a low-Reynolds-number condition. To investigate the influence of the propeller slipstream on a wing surface, the flowfield on the wing surface is visualized using a temperature-sensitive paint when the chord-based Reynolds number is equal to 3.0 x 10(4). The control surface performance improves in the installed-propeller condition because the propeller slipstream suppresses the laminar separation bubble. Finally, we suggest that the propeller should be installed ahead of the control surface to benefit from the effect of the propeller slipstream under the low-Reynolds-number flight condition.
引用
收藏
页码：228 / 235
页数：8
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