摘要
采用"亚跨超CFD软件平台"(TRIP2.0)数值模拟了30P-30N多段翼型的复杂流场,主要目的是考核湍流模型、转捩位置对多段翼型压力分布和典型站位速度型的影响。本文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,在与相应试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、不同的转捩位置对该翼型压力分布和典型站位速度型的影响。本文的研究结果表明,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,但对速度型的模拟精度较差;模拟试验的转捩位置可以改善主翼附面层与前缘缝翼边界层尾迹区的模拟精度;采用微吸气技术推迟前缘缝翼的转捩位置,可以进一步提高缝翼尾迹区的数值模拟精度。
The complex flow over 30P-30N multi-element airfoil configuration is simulated using CFD software TRIP2.0.The purpose of present work is study the effect of turbulence models and transition location to the pressure distribution and velocity profiles.By solving 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 with structured grids（1-to-1） in present paper.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;the accuracy of slat wake can be improved further when the upper transition location of slat is pushed further downstream with small suction technology.
出处
《空气动力学学报》
EI
CSCD
北大核心
2010年第1期99-103,共5页
Acta Aerodynamica Sinica
关键词
TRIP2.0
多段翼型
湍流模型
转捩位置
速度型
TRIP2.0 30P-30N multi-element turbulence model transition location velocity profile
