基于FW-H方程的直升机尾桨与涡线干扰噪声分析  

Analysis of the Helicopter Tail-rotor and Vortex Interaction Noise Based on FW-H Equation

作　　者：仲唯贵[1] 张义涛[2] 

机构地区：[1]中国直升机设计研究所,景德镇333001 [2]总参陆航部驻景德镇地区军事代表室,景德镇333001

出　　处：《直升机技术》2008年第3期31-34,共4页Helicopter Technique

摘　　要：本文通过对直升机尾桨噪声的机理进行分析,建立了尾桨与涡线干扰噪声的计算模型。计算模型中包括气动计算和声学计算,气动计算的结果作为声学计算的输入量。气动计算中分别采用三维非定常面元法计算桨叶表面压力和有扰动薄翼理论计算涡线干扰下桨叶的压力增量;声学计算中采用推导自FW-H方程的Farassat1a公式,获得声压的时间历程。通过算例分析得到了一些有意义的结论。In this paper,the tail rotor noise has been analyzed to construct the analytical model for the interaction noise of the tail rotor and the blade-tip vortex of the main rotor which includes the aerodynamic and the acoustic analysis.The aerodynamic analysis goes first to give its result as the input of the acoustic analysis.In the Aerodynamic analysis,the blade surface pressure has been calculated based on 3-D unsteady panel method and the thin airfoil theory has been employed to calculate the blade pressure jump.Acoustic analysis is based on the numerical solution of Farassat 1a formula.Some meaningful solutions have been drawn through the comparing analysis of results from theoretical analysis.

关 键 词：直升机噪声 尾桨噪声 桨涡干扰 

分 类 号：TB53[理学—物理]