NS方程计算中耦合转捩自动判断的阻力精确计算方法初探  

Accurate drag calculation by coupling automatic prediction of transition point to the Navier-Stokes method

作　　者：张坤[1] 宋文萍[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,陕西西安710072

出　　处：《空气动力学学报》2009年第4期400-404,共5页Acta Aerodynamica Sinica

基　　金：国家重点实验室基金(9140C4201020602)资助

摘　　要：在Reynolds-Averaged Navier-Stokes(RANS)方程计算中耦合了流动转捩的自动判断以提高现有求解器预测翼型阻力的准确性。由RANS方程求得翼型表面压力分布作为层流边界层方程求解的输入参数,然后使用简化的eN-数据库转捩判断方法分析层流边界层的解得到转捩点的位置,这样随着流场的迭代求解求解器自动判断转捩点的位置。在对NLF0416翼型的气动性能计算中考虑流动转捩的因素后得到的翼型升阻力特性和实验吻合较好,验证了本文方法的正确性。In this paper, we couple automatic prediction of transition to the calculation of the Reynolds- Averaged Navier-Stokes（RANS） equations in order to improve the accuracy of drag prediction in our flow solver. The RANS solver calculates the surface pressure distribution of the airfoil and communicates as input data to the laminar boundary-layer method compute all of the boundary-layer parameters and then the simply e^N-database method determines new transition positions which given back to the RANS solver. So it is a automatic progress of transition prediction. This method is used to simulate the flow around the NLF0416 airfoil and the calculation results are in concordance with the experimental data.

关 键 词：RANS方程 层流边界层 转捩判断 eN-数据库方法 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]