多段翼型高精度数值模拟技术研究  

High-order numerical study of complex flow over multi-element airfoil

作　　者：王运涛[1] 孟德虹[1] 邓小刚[1] 

机构地区：[1]中国空气动力研究与发展中心空气动力学国家重点实验室,四川绵阳621000

出　　处：《空气动力学学报》2013年第1期88-93,共6页Acta Aerodynamica Sinica

基　　金：国家重点基础研究发展计划;项目编号2009CB723800

摘　　要：采用五阶精度的加权紧致格式(WCNS)数值模拟了NLR7301两段翼型、30P-30N三段翼型的复杂流场,主要目的是考核WCNS格式模拟多段翼型复杂流场的能力,研究湍流模型、转捩位置对多段翼型压力分布和典型站位速度型的影响。通过求解任意坐标系下的雷诺平均的N-S方程,采用多块对接结构网格技术,在与相应实验结果对比的基础上,详细研究了SA一方程湍流模型、SST两方程湍流模型、转捩位置对该翼型压力分布和典型站位速度型的影响。研究结果表明,基于WCNS格式,采用全湍流模拟方式可以较好地模拟该多段翼型的压力分布,但对边界层速度型和阻力系数的模拟精度较差;模拟实验的转捩位置可以改善边界层和尾迹区的模拟精度,提高阻力的数值模拟精度。The complex flow over NLR7301 and 30P-30N multi-element airfoil configuration is simulated using five-order weighted compact nonlinear scheme（WCNS）. The purpose of present work is study the effect of turbulence models and transition location to the pressure distribution and velocity profiles. By sol- ving Reynolds averaged Navier-stokes equation in arbitrary coordinates and comparing to test results, the effect of SA and SST turbulence models and transition location are carefully study in present paper with structured grids（I-to-I）. The numerical results show that pressure distribution are in good agreement with experiment with fully turbulent calculation, whereas poor velocity profiles are obtained ;the accuracy of the boundary layer of the main element and the slat wake are improved significantly when the transition locations from the test are taken into account, and the accuracy of drag coefficient prediction is improved also.

关 键 词：WCNS 多段翼型 湍流模型 转捩位置 速度型 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]