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

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.