Wing Rock Induced by Forebody Asymmetric Vortex in Coning Motion and its Control Method

被引：1

作者：

Wu, G. X. ^{[1
]}

Deng, X. Y. ^{[1
]}

Wang, Y. K. ^{[1
]}

Xu, S. W. ^{[1
]}

Tian, W. ^{[1
]}

机构：

[1] BeiHang Univ, Minist Of Educ, Key Lab Fluid Mech, Beijing 100191, Peoples R China

来源：

7TH ASIAN-PACIFIC CONFERENCE ON AEROSPACE TECHNOLOGY AND SCIENCE, APCATS 2013 | 2013年 / 67卷

关键词：

Wing rock; forebody asymmetric vortices; coning motion; perturbation control; high angle of attack aerodynamics; SLENDER BODY; VORTICES; AIRCRAFT; FLOW;

D O I：

10.1016/j.proeng.2013.12.028

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

An experimental investigation of wing rock induced by forebody vortex in coning motion over wing/body model with sweep angle of 30 degrees and its control method has been conducted in wind tunnel at angle of attack of 50 degrees and Reynolds number of 1.56x10(5) based on the diameter of the cylinder body with free-to-roll equipment. Firstly, wing rock pattern is determined by nose tip perturbation in coning motion, which is same as the static case. Secondly, coning rate has no effect on the frequency and amplitude of wing rock. Finally, wing rock can be suppressed by control technique of rotating nose perturbation also. (C) 2013 The Authors. Published by Elsevier Ltd.

引用

页码：288 / 294

页数：7

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