摘要
为满足电控旋翼的设计需要,首先给出了可计及襟翼移轴补偿影响的带襟翼翼型的综合时域非定常气动力计算模型。以此为基础,对襟翼弦长比和移轴补偿率这两个重要参数进行了分析。结果表明:增大移轴补偿率会减小升力系数;俯仰力矩系数随襟翼弦长比增大将出现最值,该最值与移轴补偿率有关;襟翼铰链力矩系数随襟翼弦长比增加迅速增大,而增加移轴补偿率则可大幅度减少襟翼铰链力矩系数。对于电控旋翼而言,襟翼弦长比取0.2左右,移轴补偿取0.25左右,可以取得较为满意的效果。
In order to satisfy the design of Electrical Controlled Rotor(ECR),a synthetic unsteady aerodynamic model in time do- main is presented to predict the aerodynqmic force and moment of the airfoil with a flap.This model can take account of the effect of flap nose overhang.Based on the validated model,parameter analysis about flap chord ration and nose overhang is executed and some conclusions are obtained.The lift coefficient is decreasing with the increase of flap nose overhang.Increasing the flap chord ration,the pitching moment coefcient will appear a peak which is related with nose overhang,while the flap hinge moment coeffi- cient will go up rapidly.In order to reduce the flap hinge moment,a nose overhang should be adopted.For the application to Elec- trical Controlled Rotor,the value of 0.2 chord ration and 0.25 nose overhang would be suitable.
出处
《直升机技术》
2004年第3期18-22,共5页
Helicopter Technique
关键词
电控旋翼
襟翼
非定常气动力
弦长比
移轴补偿
electrical controlled rotor
flap
unsteady aerodynamic
chord ration
nose overhang
