模型振动对风洞实验数据分散性的数值模拟研究  

Numerical Simulation Study on Aerodynamic Data Scatter Phenomena for Vibrating Models in Wind Tunnel Measurements

作　　者：龙垚松[1,2] 叶正寅[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国防科技重点实验室,西安710072 [2]中国三江航天工业集团公司设计所,武汉430040

出　　处：《航空工程进展》2012年第2期131-137,共7页Advances in Aeronautical Science and Engineering

基　　金：国家自然科学基金(10872171)

摘　　要：研究模型振动对风洞实验结果的影响对于修正风洞实验数据和加深空气动力学的理解具有重要的现实意义。基于k-ω的SST两方程湍流模型,在时间域求解雷诺平均N-S方程,研究了模型振动在不同迎角下流场和气动力的变化规律。结果表明:模型振动在小迎角条件下对气动力测量结果几乎没有影响,但在大迎角存在一定分离的条件下,可以引起分离涡的非线性演化,导致气动力平均值的改变,从而引起风洞气动力测量值的分散性。结论从物理机理上解释了大迎角风洞实验的重复性和数据分散性。Studying the influence of model vibrating in wind tunnel measurements is of important realistic mean ings for modifying wind tunnel test data and deepening aerodynamics understanding. Coupled with SST κ-ω turbulent model, the unsteady Reynolds-averaged Navier-Stokes equations are solved in the time-domain. The flow fields and aerodynamic characteristics for vibrating airfoils at different incidences are investigated systematically. From the large amount of numerical simulation data, the vibration of the airfoil for the wind tunnel models cannot affect the measurement results in small incidences. But if the airfoil has some separation over the upper surface, the vibration will lead to the nonlinear variation so that the average aerodynamic coefficient value changes, these phenomena will result in the scatter in wind tunnel measurements for models in large incidences. In terms of physics mechnism, these results can be used to explain the poor repeatability and scatter phenomena of aerodynamic characteristics for configurations at high incidences in wind-tunnel experiments,

关 键 词：模型振动 分离流 风洞实验 分散性 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]