不同部件对机翼摇滚特性影响的风洞试验研究  

Investigation on Wing Rock in a Low Speed Wind Tunnel for Fighter with Different Configurations

作　　者：姜裕标[1] 孙海生[1] 张钧[1] 李宝[1] 

机构地区：[1]中国空气动力研究与发展中心低速所,四川绵阳621000

出　　处：《飞行力学》2002年第4期39-43,共5页Flight Dynamics

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.

关 键 词：机翼 摇滚特性 影响 风洞试验 战斗机 气动布局 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程] V211.