摘要
介绍了机翼摇滚低速风洞试验技术，并对试验装置、试验方法、数据采集等进行了描述。重点讨论了一种歼击机模型在气动中心低速所4m×3m风洞进行的机翼摇滚风洞试验的典型结果。最后对形成机翼摇滚的机理进行了探讨与分析。
The wing rock test technique in low speed wind tunnel is presented in this paper,including test apparatus and test methods as well a s data acquisition. The typical test results about wing rock for a fighter confi guration conducted in CARDC 4m×3m low speed wind tunnel are also discussed brie fly. Finally,the mechanism of wing rock is explored.
出处
《流体力学实验与测量》
EI
CSCD
2000年第4期32-35,40,共5页
Experiments and Measurements in Fluid Mechanics
关键词
大攻角
机翼摇滚
风洞试验
high angle of attack
wing rock
wind tunnel test
