摘要
提出一种前进比高达0.8的旋翼气动特性分析方法,该方法针对高前进比旋翼前行桨叶压缩性、后行桨叶失速效应严重以及桨叶偏流作用和反流区大的特点,建立了旋翼气动力模型以及与之相适应的旋翼诱导速度时变非均布模型与桨叶非定常挥舞运动模型,然后根据高前进比旋翼气动力、旋翼诱导速度和桨叶挥舞运动三者之间的内在耦合关系提出了高前进比旋翼气动特性的动态响应计算方法,最后以H-34旋翼为例计算了该旋翼高前进比状态的气动特性,并将计算结果与风洞试验数据进行对比验证,结果合理。
A method to predict the aerodynamic characteristics of rotor with advanced ratio up to 0.8 is proposed.An aerodynamic model is established for the high advanced ratio rotor with the compressibility of advancing blade,stall effect and large reverse flow region of retreating blade as well as great sweep flow on the blade.A time-vary and non-uniform induced velocity model and unsteady flap motion model of blade are set up to adapt to the rotor aerodynamic model.A computational method of dynamic response for predicting the aerodynamic characteristics of high advanced ratio rotor was developed based on the inherent coupling relationship among rotor aerodynamics,rotor induced velocity and blade flap motion.Finally,H-34 rotor is taken to calculate its aerodynamic characteristic with various combinations of advanced ratio and rotor attack angle and the results are compared with the wind tunnel test data.The results show that the method can predict the aerodynamic characteristic of high advanced ratio rotor reasonably.
出处
《空气动力学学报》
EI
CSCD
北大核心
2011年第5期542-547,共6页
Acta Aerodynamica Sinica
关键词
高前进比旋翼
挥舞运动
诱导速度
气动特性
反流区
high advanced ratio rotor
flapping motion
induced velocity
aerodynamic characteristics
reverse flow region
