湍流模型对三维翼梢涡流场数值模拟的影响  

Effect of Turbulence Models on Numerical Simulation of Tip Vortex Flow Field Behind 3D Wing

作　　者：韩宝玉[1] 熊鹰[1] 叶金铭[1] 

机构地区：[1]海军工程大学船舶与动力学院,湖北武汉430033

出　　处：《航空学报》2010年第12期2342-2347,共6页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(51079157);海洋工程国家重点实验室基金(0811)

摘　　要：梢涡流场数值模拟对减少梢涡的不良影响意义深远。应用雷诺平均Navier-Stokes(RANS)方法建立了三维翼梢涡流场数值模型,选用的湍流模型包括两种经典两方程模型和一种代数雷诺应力模型。计算内容包括翼梢涡流场速度分布、压力分布及涡核位置,为了准确模拟梢涡涡核内系统旋转和流线曲率影响,将旋转和曲率修正方法应用于选用的湍流模型中。计算时对翼梢涡涡核处网格进行了加密处理。将计算结果与实验结果对比后发现,修正后的湍流模型较标准湍流模型明显提高了预报精度,与实验结果吻合较好,具有工程应用价值。Numerical simulation of a tip vortex flow field is significant in alleviating the effect of the tip vortex.A model based on the Reynolds-averaged Navier-Stokes（RANS）method is established to simulate the tip vortex flow field behind a 3D wing.The turbulence models selected include two classic two-equation models and one explicit algebraic Reynolds stress model.The calculation contains the velocity distribution,pressure distribution and the vortex core location of the tip vortex flow field.To consider the effect of system rotation and streamline curvature,a rotation-curvature correction is adopted to each turbulence model.Mesh refinement is applied to the area of the tip vortex core in simulation.Numerical results show that the corrected eddy viscosity turbulence models agree well with experiment results in velocity and pressure distribution and vortex core location.Compared with the unmodified versions,they exhibited remarkable improvement in predicting turbulence induced diffusion.

关 键 词：湍流模型 旋转和曲率修正 梢涡 数值模拟 涡核 

分 类 号：V211.17[航空宇航科学与技术—航空宇航推进理论与工程] U661.31[交通运输工程—船舶及航道工程]