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基于湍流Navier-Stokes方程,建立了一套直升机涵道尾桨流场及气动特性的CFD分析方法。在该方法中,针对直升机涵道尾桨流场的特点以及动量源方法对网格系统的要求,提出了一种多块对接网格生成方法,分块贴体网格采用求解Poisson方程的方法生成。通过结合涵道尾桨的运动方式、几何特征及气动特征,建立一个包含动量源项的N-S方程的涵道尾桨流场计算方法和迭代流程;为较好地捕捉涵道壁附近存在的旋涡及分离现象,采用了一方程S-A湍流模型。通过对ONERA M6机翼的绕流特性的计算分析,以及对涵道尾桨在悬停状态下的拉力、诱导速度、载荷分布等的计算分析,验证了该CFD方法的有效性。在此基础上,采用该方法进行直升机悬停、侧飞和前飞状态下涵道尾桨流场与气动特性的数值分析,得到了关于涵道尾桨流场和气动特性的一些有意义的结论。
Based on the turbulent Navier-Stokes equations, a set of CFD analysis methods for the flow field and aerodynamic characteristics of tail rotor of a helicopter is established. In this method, aiming at the characteristics of tail rotor flow field of helicopter and the requirement of the momentum source method for the grid system, a multi-patch docking mesh generation method is proposed. The patch-in-patch mesh method is used to solve the Poisson equation generate. By combining with the motion, geometrical characteristics and aerodynamic characteristics of the tail rotor, a method of calculating the tail rotor flow field and the iterative flow of NS equations containing momentum sources are established. In order to better capture the vortex And the phenomenon of separation, using an equation SA turbulence model. Through the calculation and analysis of the flow around the ONERA M6 wing and the calculation and analysis of the drag force, the induced speed and the load distribution of the tail rotor in the hovering state, the effectiveness of the CFD method is verified. On this basis, the numerical analysis of the flow field and aerodynamic characteristics of the rotor tail rotor at hovering, side-flying and forward-flying states is carried out by this method. Some meaningful results on the flow field and aerodynamic characteristics of the tail rotor are obtained. in conclusion.