桨叶结冰对尾桨气动性能的影响

Influence of Blade Icing on the Aerodynamic Performance of a Tail Rotor

基于某直升机尾桨桨叶地面结冰试验数据，建立了结冰桨叶的气动计算模型。对NACA0012翼型的气动特性计算表明，翼型升力系数和阻力系数的计算结果与试验数据吻合良好。然后根据所建模型，利用Fluent软件分别计算了某尾桨桨叶翼型结冰前后剖面的气动特性，发现结冰使桨叶翼型升力系数降低，阻力系数增大。最后采用动量一叶素理论结合的方法计算了该尾桨结冰前后的气动性能。结果表明，结冰使尾桨拉力系数降低而扭矩系数上升，严重恶化了尾桨的气动性能。

Based on the ground icing-test data of a certain type of helicopter tail rotor, an analytical model of iced rotor aerodynamic performance was established. It was found that the lift and drag coefficients of NACA0012 blade section airfoil by the model correlated well with test data. Based on the established model, the characteristics of tail rotor blade airfoil was calculated both for clear and iced situations by Fluent code The results showed that icing reduced the lift coefficient and increased the drag coefficient of blade airfoil. At last, a method to analyzing aerodynamic characteristics of tail rotor on icing condition was formulated by using element -momentum theory in combination. The final results showed that icing could reduce the thrust coefficient and increase the torque coefficient, which significantly deteriorated the aerodynamic performance of the tail rotor.