人工微扰动对前体非对称涡诱导机翼摇滚运动的影响特性
首发时间:2012-09-29
摘要:采用细长旋成体类型前机身的飞行器在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,通过风洞实验,研究了固定攻角下人工微扰动周向位置对前体非对称涡诱导机翼摇滚运动的影响特性。研究表明,随着攻角的增加,前体非对称涡随人工扰动周向位置的变化将先后呈现出连续态和双稳态两种演化规律。当前体非对称涡随扰动位呈现连续态变化时,扰动周向位置的变化将诱导出三种机翼摇滚运动形态:振荡发散、发散和微振。而当前体非对称涡随扰动位呈现双稳态变化时,则会出现单极限环运动、不规则运动和微振三种运动形式。
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Effect of Micro-perturbation on the Wing Rock Motion Induced by Different Forebody Asymmetric Vortices
Abstract:The wing rock phenomenon induced by forebody asymmetry vortices is liable to occur on modern aircrafts with pointed ogive-cylindrical forebody flying at large angle of attack. The paper investigated the effect of circumferential location of artificial micro-perturbation closed to the nose tip on the wing rock motion induced by different forebody asymmetric vortices over the model of a pointed ogive-cylindrical body with 30 swept wings at the fixed angles of attack in the wind-tunnel. Results show that the variation of forebody asymmetric vortices with the perturbation location will change from consecutive to bistable as angle of attack increased. Under the condition of consecutive asymmetric vortices, the wing rock motion exhibits three types of oscillation when the perturbation location is changed: oscillating divergence, divergence, equilibrium state with tiny oscillation. And three types of oscillation including limit cycle oscillation, equilibrium state with tiny oscillation, irregular oscillation will happen when the model is dominated by bistable asymmetric vortices.
Keywords: fluid mechanics artificial micro perturbation forebody asymmetric vortices wing rock
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