摘要
简要介绍了机翼摇滚低速风洞试验技术研究 ,对试验装置、试验方法、数据采集等进行了描述。重点讨论了不同部件对机翼摇滚特性影响的风洞试验研究结果。结果表明 :机翼摇滚是不依赖于初始滚转角的滚摆现象 ,出现机翼摇滚现象的起始迎角在滚转阻尼导数反号处 ;飞机不同布局以及不同部件对机翼摇滚特性有显著影响。
The wing rock test technique in a low speed wind tunnel was presented in this paper, including a test apparatus and test methods as well as data acquisition. The typical test results about wing rock for fighters with different configurations conducted in CARDC 4 m×3 m low speed wind tunnel were also discussed briefly. Conclusions based on the results were the following: Wing rock is independent of initial roll angles. Wing rock occurs at a moderate to high angles of attack, at which the rolling damp changes from negative to positive.Wing rock is greatly affected by different configurations and components of a fighter.
出处
《飞行力学》
CSCD
2002年第4期39-43,共5页
Flight Dynamics
