复合式高速直升机旋翼下洗流对机翼的气动影响分析  

Aerodynamic effect analysis of rotor downwash on wings of composite high-speed helicopter

作　　者：刘超凡 朱清华[1] 刘佳 LIU Chaofan;ZHU Qinghua;LIU Jia(National Key Laboratory of Rotorcraft Aeromechanics,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室,南京210016

出　　处：《航空工程进展》2023年第1期38-46,共9页Advances in Aeronautical Science and Engineering

摘　　要：对复合式高速直升机的旋翼两侧不同强度下洗流对机翼的气动干扰分析,可以为类似构型直升机的气动外形设计及优化提供一定的参考。采用动量源方法对复合式高速直升机悬停及前飞状态的流场进行数值模拟,分析旋翼两侧不同强度的下洗流对机翼的气动影响,研究改变旋翼桨盘高度和机翼展弦比对气动特性的影响。结果表明:复合式高速直升机前飞时,随着旋翼桨盘的增高,两侧机翼升力差峰值减小,且峰值落在更小速度处;随着机翼展弦比的增大,两侧机翼升力差峰值减小,且在峰值后同一速度下,机翼越细长两侧升力差越小。The analysis of the aerodynamic interference of the downwash on wings under different intensities on both sides of the rotor of the composite high-speed helicopter,can provide a certain reference for the design and optimization of the aerodynamic shape of the similar configuration helicopter.The unsteady momentum source method is used to perform the numerical simulation of the flow field of a composite high-speed helicopter in hovering and forward flight states,and the aerodynamic effects of different downwash on both sides of the rotor on wings are analyzed.The effect of aerodynamic characteristics on changing the height of the rotor disc and the aspect ratio of wing is studied.The results show that,when the composite high-speed helicopter flies forward,the peak lift difference between the two sides of the wing is decreased with the increase of the rotor disc height,and the peak value falls at a lower speed.With the increase of the wing aspect ratio,the peak lift difference between the two sides is decreased.Under the condition of same speed after the peak value,the slender the wing is,the smaller the lift difference between the two sides is.

关 键 词：动量源 复合式高速直升机 旋翼 机翼 气动特性 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]