Effect of bendable wing tip on aerodynamic characteristics of flying-wing configuration aircraft

被引：0
|
作者：
Liu Z. [1 ,2 ]
Jiang Y. [2 ]
Nie B. [2 ,3 ]
Cen F. [2 ]
Xu S. [2 ]
机构：
[1] School of Aeronautics, Northwestern Polytechnical University, Xi'an
[2] Low Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang
[3] College of Intelligence Science and Technology, National University of Defense Technology, Changsha
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2021年 / 42卷 / 06期
关键词：
Bendable wing tip; Directional control; Dynamic derivative; Flying-wing configuration; Wind tunnel test;
D O I：
10.7527/S1000-6893.2020.24179
中图分类号：
学科分类号：
摘要：
To improve the directional control ability of the flying-wing configuration aircraft, we design a wing tip structure which can be deflected around the direction of the wing chord based on a typical flying-wing configuration model. The static force measurement and a dynamic derivative test are conducted on the dynamic test system of the FL-14 wind tunnel. The basic aerodynamic characteristics of the flying-wing configuration aircraft and the effect of wing tip deflection on the whole aircraft are studied. The results show the static instability and extremely weak dynamic stability of the tailless flying-wing configuration aircraft in the flying direction, thereby necessitating the improvement of directional stability in both design and control of the flying-wing aircraft. The wing tip deflection is helpful to enhance the directional static and dynamic stability, and can well solve the problem of aerodynamic efficiency reduction when the traditional drag rudder is used to increase the directional stability. In addition, the wing tip deflection can also improve the deteriorated Dutch roll mode of the flying-wing configuration aircraft, bringing it closer to the conventional configuration aircraft mode that will simplify the design method of directional control law. Highly efficient with fewer rudders, the bendable wing tip is an efficient method for directional stability enhancement with high application value. © 2021, Beihang University Aerospace Knowledge Press. All right reserved.
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