Investigation of limit cycle oscillations for a wing section with nonlinear stiffness

被引：4
|
作者：
Berggren, D [1 ]
机构：
[1] Royal Inst Technol, Dept Aeronaut, SE-10044 Stockholm, Sweden
来源：
AEROSPACE SCIENCE AND TECHNOLOGY | 2004年 / 8卷 / 01期
基金：
瑞典研究理事会;
关键词：
nonlinear; aeroelasticity; structural dynamics; unsteady aerodynamics;
D O I：
10.1016/j.ast.2003.08.006
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
A wind tunnel experiment is designed with the objective to obtain well-behaved limit cycle oscillations for a wing section with two degrees of freedom, translation and rotation, in two-dimensional flow. This is accomplished using a setup of linear springs so that the resulting moment is a nonlinear function of the rotation angle. The experimental setup is designed so that the amplitudes of the limit cycle oscillations are sufficiently low to motivate the use of linear aerodynamics in the analysis. The experimental results are compared to analyses for two different configurations, and the agreement is fairly good. (C) 2003 Elsevier SAS. All rights reserved.
引用
收藏
页码：27 / 34
页数：8
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