基于转捩/尺度适应模型与FW-H声学方程的气动噪声数值模拟研究  

Research of the aeroacoustic noise simulation based on transition/scale-adapt model and FW-H equation

作　　者：王丹[1] 白俊强[1] 黄江涛[1,2] 华俊 董建鸿[4] 

机构地区：[1]西北工业大学航空学院,西安710072 [2]中国空气动力研究与发展中心,绵阳621000 [3]中国航空研究院,北京100012 [4]中国航空工业集团公司第一飞机设计研究院,西安710089

出　　处：《计算力学学报》2013年第5期704-711,共8页Chinese Journal of Computational Mechanics

摘　　要：采用计算流体力学(CFD)同"声类比"相结合的方法进行噪声模拟,利用CFD数值模拟MD30P30N多段翼型失速攻角附近流场以及其气动特性来校核近场精度,进一步通过结合可穿透数据面的FW-H声学方程进行气动噪声分析。为了准确捕捉近场流场信息,为噪声预测提供可靠的声源精度,本文基于k-ω剪应力输运(SST)湍流模型,建立了尺度适应分离流(SAS)模型,并采用γ-Reθt转捩模型耦合k-ωSST湍流模型建立了边界层转捩数值模拟技术;充分利用尺度适应模型在边界层表现为雷诺平均(RANS)方法这一特点,将γ-Reθt转捩模型与SAS模型结合,建立针对包含转捩、分离现象复杂流场的数值模拟技术。文中以RANS为控制方程,分别采用全湍流k-ωSST模型、γ-Reθt SAS转捩/分离流模型对多段翼进行近场数值模拟计算,结合可穿透数据面的FW-H声学方程进行气动噪声预测,在分析其对流场及气动噪声影响的基础上,得出了几点结论。Combined the computational fluid dynamics （CFD） numerical simulation and the acoustics analogy method,the noise simulation on the multi-element airfoil of MD30P30N is presented. The CFD numerical simulation is used to compute the flow around MD30P30N multi-airfoil at the stall angle, and then the FW-H acoustics equation is combined to compute the aerodynamic noise. For giving the precise CFD result as the sound source,the scale-adaptive simulation of separate flow model which based on SST turbulent and the boundary transition simulation method which gives the coupling to γ- Reθt transition model and SST turbulent model are established. The scale-adaptive separate （SAS） flow model behaves the characters of the RANS method at the boundary layer. Based on the combination of the SAS model and the y- Reθt transition model, the numerical simulation technique including transition and separation for the complex flow is constructed. With the RANS equation as the control equation,the full turbulent simulation through the k-ω SSTmodel and the simulation through the γ-Reθt -SST-SAS transition model are used to compute the multi-element airfoil flow, respectively. The aerodynamic noise is computed through the FW-H equation based on the CFD solution. The results are analyzed at the aerodynamic view and the aerodynamic noise view, and several conclusions are given at the end of the paper.

关 键 词：气动噪声 FW-H声学方程 γ- Reθt转捩模型 尺度适应模型 转捩 分离流模型 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]