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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 new aerodynamic performance analysis method of rotor with a forward ratio of up to 0.8 is proposed in this paper. In view of the characteristics of forward advancing blade compressibility, serious stalling effect of rear propeller blade, large blade bias effect and large reflux area, Rotor aerodynamic model and its corresponding rotor-induced velocity time-varying non-uniform model and blade unsteady waving motion model, and then according to the high advance than the rotor aerodynamic force, rotor induced speed and blade waving movement between the three In the end, the aerodynamic characteristics of rotor with high forward ratio are calculated by taking H-34 rotor as an example. The calculated results are contrasted with the wind tunnel test data. The result is reasonable.