有侧壁干扰的机翼半模型风洞实验的N-S方程数值模拟  

NAVIER-STOKES CALCULATION OF WIND TUNNEL TESTING OF SEMISPAN WING WITH SIDE-WALL INTERFERENCE

作　　者：焦予秦[1] 乔志德[1] 

机构地区：[1]西北工业大学翼型研究中心,陕西西安710072

出　　处：《航空学报》2001年第2期140-143,共4页Acta Aeronautica et Astronautica Sinica

摘　　要：应用三维可压、雷诺平均 Navier-Stokes方程数值模拟了机翼半模实验风洞侧壁干扰和三维机翼半模与安装侧壁结合部流场。计算采用中心有限体积多步 Runge-Kutta时间步长格式 ,将 Baldwin-Lomax两层代数紊流模型扩展应用于三维拐角区流动。用本文方法计算了 3个算例 ,并与国外的有关实验数据进行比较 。A cell centered finite volume scheme that applies a multistage time stepping scheme in conjunction with steady state acceleration techniques is used to solve the integral form of mass averaged three dimensional Navier Stokes equations for flows over a swept NACA0012 wing and a thin low aspect ratio wing mounted in a wind tunnel. Attention is given to various aspects of computation of viscous side wall effects on the flow around a wing. These include the extension of the Baldwin Lomax turbulence model to compute flows in junctures and the treatment of the boundaries of the computational domain. Results for different wings are compared to free air Navier Stokes solutions and to experimental data. It is shown that the pressure distributions at 3 spanwise locations compare well with the experimental data, many of the flow features typical of junction flow have been predicted and the effects of the viscous side wall on flow pattern over the wing surface, particularly in the vicinity of the wing/wall juncture, are significant.

关 键 词：风洞侧壁干扰 NAVIER-STOKES方程 有限体积法 拐角区流动 机翼半模型 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程] V211.41