共轴刚性旋翼气动特性试验与分析

在航空工业气动院FL-52风洞开展了共轴刚性旋翼气动特性风洞试验，通过合理的操纵与配平策略，实现了共轴刚性旋翼配平，并对悬停、多种前飞状态下气动特性及升力偏置对旋翼操纵特性及性能的影响机理进行了研究。结果表明，试验取得了比较好的配平效果，桨毂力矩、合扭矩及升力偏置配平误差分别优于±2 N·m、±0.5 N·m、±0.01；悬停状态扭矩配平与非配平状态下，上旋翼效率都大于下旋翼；前飞状态升力偏置可有效提升大前进比时旋翼气动效率而小前进比时则并不明显，升力偏置的增大会使上下旋翼的桨毂滚转力矩大幅增加。

Experiment and Analysis of Aerodynamic Performance of Coaxial Rigid Rotor

A coaxial rigid rotor trim strategy was developed and the wind tunnel test was carried out in the FL-52 wind tunnel of AVIC Aerodynamics Research Institute to investigate the performance of coaxial rigid rotor. The rotor aerodynamic performance in hover and forward flight conditions and the influence of lift offset were studied. The results indicate that the trim strategy is reasonable, and the trim?results?are?satisfactory; The trim errors of hub torque, total torque of rotors and lift offset are better than ±2 N·m, ± 0.5 N·m and ± 0.01 respectively, The efficiency of the upper rotor is greater than that of the lower rotor under torque balanced and unbalanced in hover; In forward flight, The lift offset in forward flight can effectively improve the rotor aerodynamic efficiency at high forward ratio, but it is not significant at low forward ratio,increasing the lift offset will significantly increase the hub rolling moment of the upper and lower rotors.