直升机尾桨涡环飞行试验研究  

Flight Test Research on Helicopter Tail Rotor Vortex Ring

作　　者：汤连刚[1] 朱宇[2] 李显耀[2] 秦超敏[2] 

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]中国飞行试验研究院飞机所,陕西西安710089

出　　处：《飞行力学》2008年第5期63-66,共4页Flight Dynamics

摘　　要：根据样机右侧飞的飞行试验,对尾桨涡环现象进行了计算分析;根据右侧飞试验结果,估算出样机悬停回转时尾桨处于涡环状态的偏航角速度范围;将试验结果与国内外的涡环状态判据进行了对比。结果表明,国外的涡环判据不适用于样机的尾桨涡环状态判定,国内的高-辛判据与试验结果一致。In this paper, the helicopter tail rotor vortex ring has been calculated and analyzed, according to the result of the rightward level side flight test of the sample helicopter. The range of yawing rate when turning left in hover is calculated with some overseas and some others is , where the tail rotor might get into vortex ring. The Gao-Xin criterion of vortex ring is compared criteria. The analysis shows that the Gao-Xin criterion is consistent with the result of flight test, not appropriate for determining the tail rotor getting into vortex ring of the sample helicopter.

关 键 词：尾桨涡环 侧飞 悬停回转 涡环判据 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]