Design and Experiment Study of Coanda Surface at Airfoil Trailing Edge

被引：0
|
作者：
Liu Hongyang [1 ]
Hu Buyuan [2 ]
Song Chao [1 ]
Zhou Zhu [1 ]
Yu Yonggang [1 ]
Tang Yu [1 ]
机构：
[1] China Aerodynam Res & Dev Ctr, Computat Aerodynam Inst, Mianyang, Peoples R China
[2] China Aerodynam Res & Dev Ctr, Low Speed Aerodynam Inst, Mianyang, Peoples R China
来源：
2023 ASIA-PACIFIC INTERNATIONAL SYMPOSIUM ON AEROSPACE TECHNOLOGY, VOL II, APISAT 2023 | 2024年 / 1051卷
关键词：
Jet Circulation Control; Coanda Surface; Design and Optimization; Numerical Simulation; Wind Tunnel Test;
D O I：
10.1007/978-981-97-4010-9_136
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
The flying-wing aircraft has good aerodynamic and stealth performance but poor attitude control capability. The jet circulation control (JCC) technology is the most widely used, which changes circulation by blowing air at the wing trailing edge to form the Coanda effect. The design method of 2D Coanda profile is proposed, which can increase pitch control efficiency obviously. The Coanda profile that matches the jet slot height of 0.30 mm is designed under Mach number 0.6. The flow control mechanism of Coanda profiles with and without steps are analyzed deeply. JCC effect of airfoil including different jet devices under Mach number 0.5 is studied with wind tunnel test and computational fluid dynamics (CFD). The research results indicate that the design method of 2D Coanda profile proposed is feasible and effective. The simulation capability of CFD at jet circulation control is verified further by wind tunnel tests. It can be developed to the research of the flying-wing aircraft without control surfaces based on JCC technology. It is promising to solve attitude control difficulties of the flying-wing layout.
引用
收藏
页码：1752 / 1764
页数：13
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