摘要
自由尾迹的桨叶气动模型中,考虑了由于桨叶预扭导致尾随涡不在同一个平面对控制点诱导速度的影响,翼型气动模型采用Leishman-Beddoes非定常气动模型,并推导得到操纵下的桨叶挥舞运动方程。采用二阶精度时间步进格式,耦合桨叶气动模型、挥舞运动方程,构建时间步进自由尾迹算法。而后计算旋翼尾迹在操纵条件下的变化历程,得到旋翼的气动响应。通过计算结果与实验数据的对比,验证方法的可行性,并分析操纵速率、预扭对气动响应的影响。
The influence of near wake trailers in different planes due to blade twist was accounted into Blade aerodynamic model in free wake.Leishman-Beddoes unsteady aerodynamic model was applied to airfoil model,and flapping equation of blade under manoeuvering was derived.Time-step free wake was established by coupling second-order time accurate algorithm,blade aerodynamic model,blade flapping equation and rotor trim.Then time histories of wake geometry and aerodynamic response were calculated.The time-step method was feasible by comparing the result with experimental data,and then the influence of pitch rate and pre-twist on aerodynamic response was analyzed.
出处
《空气动力学学报》
EI
CSCD
北大核心
2011年第2期217-221,共5页
Acta Aerodynamica Sinica
关键词
自由尾迹
总距突增
旋翼
气动响应
时间步进
预扭
free wake
ramp increased pitch
rotor
aerodynamic response
time-step
pre-twist
