摘要
基于叶素理论和滑流理论,建立了悬停状态直升机倾斜式尾桨诱导速度的计算方法,在此基础之上,根据高正-辛宏理论,并考虑到倾斜式尾桨的倾斜角,对直升机倾斜式尾桨涡环侧飞速度边界进行了预测,并与飞行试验结果进行了对比,结果表明,预测方法计算所得的倾斜式尾桨涡环状态与飞行试验结果较为吻合,该方法可对直升机倾斜式尾桨涡环进行有效地预测。
Based on the blade element theory and slipstream theory, the method calculating induced velocity of the helicopter tail rotor in hover was established. And on this basis, according to the Gao-Xin theory and considering the inclination angle of the tilting tail rotor, the helicopter tilting tail rotor vortex ring was predicted and compared with the data of flight test. The results show that the calculation of the tilting tail rotor vortex ring is in good agreement with the flight test results. The method can be applied to effectively predict the helicopter tilting tail rotor vortex ring.
作者
孟晓伟
张宏林
杨文凤
Meng Xiaowei;Zhang Honglin;Yang Wenfeng(Chinese Flight Test Establishment, Xi＇an 710089, China)
出处
《航空科学技术》
2018年第1期58-62,共5页
Aeronautical Science & Technology
关键词
倾斜式尾桨
尾桨涡环
叶素理论
滑流理论
高正一辛宏理论
飞行试验
直升机
tilting tail rotor
tail rotor vortex ring
blade element theory
slipstream theory
Gao-Xin theory
flight test
helicopter
