旋翼翼型流动分离特性分析及高升力设计  

Analysis of Rotor Airfoil Flow Separation Characteristics and High Lift Design

作　　者：王雪鹤 张子瀚 柴春硕 邢世龙 袁明川[1] WANG Xuehe;ZHANG Zihan;CHAI Chunshuo;XING Shilong;YUAN Mingchuan(Science and Technology on Rotorcraft Aeromechanics Laboratory,China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所直升机动力学全国重点实验室,江西景德镇333001

出　　处：《直升机技术》2023年第3期1-8,15,共9页Helicopter Technique

摘　　要：旋翼翼型的失速特性影响了直升机旋翼在前飞和机动工况下的气动性能。采用CFD数值模拟方法,对OA212、OA206两种不同厚度旋翼翼型的大攻角分离流场进行分析,分别展现了后缘分离和前缘分离两种分离形态,并从压力分布的角度解释了引发不同分离形式的流动机理。然后从流动机理出发,开展了两个旋翼翼型的关于提升最大升力的参数影响研究。结果表明,增加OA212翼型的前缘曲率并减小后部反弯度,可有效抑制后缘分离涡,进而提升最大升力;而对于薄翼型OA206,无法通过微调前缘有效改善前缘分离特性。The stall characteristic of rotor airfoil effects aerodynamic of helicopter rotor in forward and maneuvering flight.Numerical simulated and analysed separate flow field of two different thickness airfoil OA212 and OA206 at high angle of attack using CFD method,and shown two different separate forms including trailing edge separation and leading edge separation,then explained the flow mechanism for different separation form from the point of pressure distribute.Based on the flow mechanism,studied parameter influence about how to elevate the maximum lift coefficient for these two airfoils.Results shown that,for thick airfoil,it can effectively restrain trailing edge separation and promote the maximum lift coefficient by increasing leading edge curvature and decreasing rear reverse camber of OA212,but it did not work by adjusting leading edge shape to improve leading edge separation characteristic for thinner airfoil OA206.

关 键 词：旋翼翼型 失速 数值模拟 流动分离 

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]