基于变桨与襟翼协同的降载特性研究及机理分析  

Research on Load Reduction Characteristics and Mechanism Analysis Based on Synergy Between Pitch and Flap

作　　者：白冬晓 王冰[1] 李寅生 王万成[1] BAI Dongxiao;WANG Bing;LI Yinsheng;WANG Wancheng(School of Energy and Power Engineering,Hohai University,Nanjing 211100,China)

机构地区：[1]河海大学能源与电气学院,南京211100

出　　处：《动力工程学报》2024年第7期1068-1074,共7页Journal of Chinese Society of Power Engineering

基　　金：国家重点研发计划资助项目(2022YFB4201303)。

摘　　要：研究了尾缘襟翼长度、偏转角和攻角对翼型降载特性的影响,并分析其影响机理。结果表明:变桨与尾缘襟翼的协同控制可有效实现挥舞方向上的降载;尾缘襟翼长度越大,尾缘偏转角越小,攻角越远离临界值,降载性能越佳;偏转角增大会导致临界攻角位置前移;为实现快速降载,在正偏转角、大攻角下优先选择尾缘控制,其他情况下均优先选择变桨控制;降载特性与翼型及翼缝流体分布密切相关,压差越小,降载性能越好。The effects of trailing flap length,deflection angle and angle of attack on the load reduction characteristics of airfoil were studied,and the influence mechanism was analyzed.Results show that the cooperative control of the pitch and the trailing flap can effectively realize the load reduction in the swing direction.The larger the length of the trailing flap,the smaller the trailing edge deflection angle.The farther away from the critical value of the angle of attack,the better the load reduction performance.The increase of the deflection angle will lead to the forward movement of the critical angle of attack.The tail edge control is preferred under the positive deflection angle and the large angle of attack,and the pitch control is preferred in other cases.The load reduction characteristics are closely related to the fluid distribution of the airfoil and wing slots,and the smaller the pressure difference,the better the load reduction performance.

关 键 词：法向力系数 静压 尾缘襟翼长度 襟翼偏转角 攻角 

分 类 号：TK81[动力工程及工程热物理—流体机械及工程]