高速直升机推力桨气动干扰特性研究  

Research on aerodynamic interaction characteristics of high-speed helicopter thrust propeller

作　　者：廖霆汉 曹宸恺 招启军[1] 陈希[1] 赵国庆[1] LIAO Tinghan;CAO Chenkai;ZHAO Qijun;CHEN Xi;ZHAO Guoqing(National Key Laboratory of Helicopter Aeromechanics,NUAA,Nanjing 210016,China)

机构地区：[1]南京航空航天大学直升机动力学全国重点实验室,江苏南京210016

出　　处：《飞行力学》2024年第4期13-20,共8页Flight Dynamics

基　　金：国家自然科学基金资助(12032012);重点实验室基金资助(61422202103);江苏高校优势学科建设工程资助项目。

摘　　要：针对前飞状态高速直升机全机气动干扰特性开展了研究。首先,基于动量源方法建立共轴刚性旋翼气动分析模型,并通过与试验结果对比,验证了数值模拟方法的可靠性;然后,采用滑移网格方法建立推力桨干扰的数值计算模型,采用非结构网格对机身进行划分;最后,开展了旋翼、机身、平/垂尾等对推力桨气动干扰的模拟,分析了平尾气动布局参数对推力桨气动特性的影响规律。结果表明:相较于孤立推力桨,全机干扰情况下推力桨推力系数降低、巡航效率提高;随着平尾负安装角增大,在相同推力桨总距情况下,推力桨推力系数和功率系数均增大。A research was carried out on the aerodynamic interaction characteristics of high-speed helicopters in forward flight.Firstly,a coaxial rigid rotor aerodynamic analysis model was estab-lished based on the momentum source method,and the reliability of the numerical simulation method was verified by comparing it with experimental results.Then,a numerical calculation model for thrust propeller interaction was established by using the sliding grid method,and the fuselage was divided by unstructured grid.Finally,some simulations were conducted on the aerodynamic interac-tion between rotors,fuselage,horizontal tail,vertical tail and the thrust propeller,and the influence of horizontal tail aerodynamic layout parameters on the aerodynamic characteristics of thrust propel-lers was analyzed.The results show that the thrust coefficient of the propeller in whole aircraft inter-action model decreases and the cruise efficiency increases by compared with the isolated thrust pro-peller.With the increase of the installation angle of the horizontal tail,the thrust coefficient and power coefficient of the thrust propeller increase at the same collective pitch.

关 键 词：高速直升机 推力桨 气动布局 动量源方法 滑移网格 

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]