前体非对称涡流动与单极限环自由摇滚运动之间的关系
首发时间:2013-11-20
摘要:采用细长旋成体类型前机身的飞行器在进行大攻角飞行时会产生前体非对称涡流动,进而诱发机翼摇滚。本文针对30 后掠机翼与细长旋成体机身组成的翼身组合体模型,首先给出了攻角52.5 下头尖部人工微扰动与机头非对称涡诱发机翼摇滚运动的相关关系,存在单极限环振荡、偏向一侧的微振和不规则振荡三类典型的摇滚运动形态;其次,针对单极限环运动形态,进行了相应静态状态下的流场测量,分析了摇滚运动历程中的相应位置的静态流场的演化特性,揭示了零侧滑状态下流动非对称与单极限环摇滚运动之间的相关关系。结果表明,零侧滑状态下的流动非对称是引起机翼摇滚的关键因素之一,而零侧滑状态下的横向静稳定性是决定流动出现单极限环振荡的重要因素。实验是在北京航空航天大学D4低速风洞中进行的,来流Re=1.61e5。
关键词: 流体力学 大攻角 细长旋成体和小后掠翼身组合体 机翼摇滚 非对称涡
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Relationship between the Limited Cycle Oscillation and Forebody Asymmetric Vortex Flow
Abstract:The wing rock phenomenon induced by fore-body asymmetric flow is liable to occur on modern aircrafts with pointed ogive-cylinderl forebody at large angle of attack. In this paper, three kinds of wing rock motion including limit cycle oscillation, equilibrium state with tiny oscillation, and irregular oscillation, which occur on the configuration of a pointed ogive-cylindrical body with 30 swept wing when the angle of attack is 52.5 , have been given firstly. Secondly, the relationship between the Limited Cycle Oscillation and Forebody Asymmetric Vortex Flow has also been dicussed in detail based on the flow over the forebody and wing. The result shows that the initial asymmetric flow over the fore-body and side stability namely at 0 rolling angle are the two important parameters to induce the wing rock. These tests have been finished in D4 low speed wind tuunel in BeiHang University at subcritical Reynold numer.
Keywords: Fluid Mechanics, High Angle of Attack, Wing-body Configuration,Wing Rock, Asymmetric Vortex Flow
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