Effect of rotor slipstream of tiltrotor aircraft in cruise mode

被引：0
作者：
Ma T. [1 ]
Zhang Z. [2 ]
Liu Z. [1 ]
Wang X. [2 ]
Hao S. [2 ,3 ]
机构：
[1] Institute of Unmanned System, Beihang University, Beijing
[2] School of Aeronautic Science and Engineering, Beihang University, Beijing
[3] Hiwing General Aviation Equipment Co., Ltd., Beijing
来源：
Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics | 2021年 / 47卷 / 06期
关键词：
Actuator disk; Aerodynamic characteristic; Multiple Reference Frame (MRF) model; Rotor slipstream; Sliding mesh model; Tiltrotor aircraft;
D O I：
10.13700/j.bh.1001-5965.2020.0177
中图分类号：
学科分类号：
摘要：
The tiltrotor aircraft needs to take into account the power requirements of vertical takeoff and landing and high-speed level flight, and using large diameter rotor as the propulsion device will make most of the wing in the rotor slipstream area, which is different from the conventional propeller aircraft. In order to evaluate different numerical methods and study the effect of rotor slipstream on the aerodynamic characteristics of a tiltrotor aircraft with two-blade rotor in cruise mode, the actuator disk model, the Multiple Reference Frame (MRF) model and the sliding mesh model are used respectively for numerical simulation study. The results show that, compared with no slipstream, the steady effect of slipstream increases the drag of the whole aircraft, and the maximum lift-drag ratio decreases by 7.5%. The lift generated by the tail wing is increased. The longitudinal static stability is increased by 17.1% and the pitch down moment of the whole aircraft is increased. When the angle of attack is small, although the slipstream changes the lift distribution on the wing surface, the lift of the whole aircraft does not change much. The unsteady influence of the slipstream causes periodic fluctuation of the aerodynamic characteristics of the aircraft. The fluctuation range of lift coefficient and drag coefficient are 9.0% and 10.8% respectively. With the increase of the angle of attack, the fluctuation range also increases. © 2021, Editorial Board of JBUAA. All right reserved.
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页码：1124 / 1137
页数：13
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