Wing configuration on Wind Tunnel Testing of an Unmanned Aircraft Vehicle

被引：1

作者：

Daryanto, Yanto ^{[1
]}

Purwono, Joko ^{[2
]}

Subagyo ^{[1
]}

机构：

[1] Agcy Assessment & Applicat Technol BPPT, Natl Lab Aerodynam Aeroelast & Aeroacoust, Cent Jakarta, Indonesia

[2] Agcy Assessment & Applicat Technol BPPT, Ctr Technol Def & Secur Ind, Cent Jakarta, Indonesia

来源：

5TH INTERNATIONAL SEMINAR ON AEROSPACE SCIENCE AND TECHNOLOGY | 2018年 / 1005卷

关键词：

D O I：

10.1088/1742-6596/1005/1/012032

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Control surface of an Unmanned Aircraft Vehicle (UAV) consists of flap, aileron, spoiler, rudder, and elevator. Every control surface has its own special functionality. Some particular configurations in the flight mission often depend on the wing configuration. Configuration wing within flap deflection for takeoff setting deflection of flap 20 degrees but during landing deflection of flap set on the value 40 degrees. The aim of this research is to get the ultimate CLmax for take-off flap deflection setting. It is shown from Wind Tunnel Testing result that the 20 degrees flap deflection gives optimum CLmax with moderate drag coefficient. The results of Wind Tunnel Testing representing by graphic plots show good performance as well as the stability of UAV.

引用

页数：11