Wind tunnel test of aerodynamic characteristics and parametric variation for rotor in vortex ring state

被引：0
|
作者：
Huang M. [1 ]
Wang L. [1 ]
He L. [1 ]
Yue T. [1 ]
机构：
[1] Low Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang, 621000, Sichuan
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2019年 / 34卷 / 11期
关键词：
Descent flight; Helicopter rotor; Parametric variation; Particle image velocimetry(PIV) test; Vertical wind tunnel;
D O I：
10.13224/j.cnki.jasp.2019.11.001
中图分类号：
学科分类号：
摘要：
In order to investigate the flowfield and aerodynamic characteristics of rotor in descent and vortex ring state, a BO-105 model rotor with tip Mach number similarity was tested in Φ5m vertical wind tunnel of China Aerodynamics Research and Development Center. Flowfields around blade tip in hover and descent flight were captured, and variations of rotor thrust and torque were obtained. The process of vorticity accumulation with the increase of rotor descent rate was observed through application of high speed PIV(particle image velocimetry) camera. When vertical descent rate was 0.9, rotor thrust and torque were at the lowest level, and the value was only 60% and 80%, respectively, of that in hovering state. The formation and break down of large scale vortex structure were observed in deep vortex ring state. Violent fluctuation of rotor thrust and torque in vortex ring state was caused by this phenomenon. Oblique descent had less thrust and torque loss than vertical descent. Aerodynamic characteristics of parabolic blade tip were similar with those of conventional rectangular blade tip in vertical descent. © 2019, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：2305 / 2315
页数：10
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