摘要
高精度CFD求解器是翼型设计的基础,而翼型流动转捩的准确预测是提高数值模拟精度的关键之一。eN方法是比较可靠的且可应用于翼型设计的转捩判断方法,但目前国内耦合eN转捩预测与二维雷诺平均N-S(RANS)方程求解器的研究仍需要通过求解层流边界层方程为转捩判断提供所需的边界层信息。这种方法不能处理含层流分离泡的流动。为解决上述问题,文章发展了一种直接求解RANS方程为转捩判断提供高精度的边界层解的方法,耦合基于线性稳定性理论的eN转捩判断方法实现了含层流分离泡流动的转捩点自动判断。采用文中方法对含层流分离泡的翼型绕流进行了数值模拟,转捩预测位置与实验值吻合较好,气动力计算精度得到了提高,验证了该方法的有效性。
In this paper, the transition prediction model of eN method based on linear stability theory is introduced into the calculation of the two dimensional Reynolds-Averaged Navier-Stokes （RANS） equations in order to improve the accuracy of numerical simulation of flow around airfoil, especially for cases involving laminar separation bub- bles. The detailed information of the boundary layer used for linear stability analysis is obtained from the RANS sol- ver. eN method based on linear stability theory is used to analyze this information and determine the transition posi- tion which is then returned into the RANS solver. The above steps are repeated until the transition position changes insignificantly. So it is an automatic progress of transition prediction. Numerical simulation results of flows respec- tively around $809 airfoil and NACA 663-018 airfoil, presented in Figs. 3 bles 1 and 2, and their analysis confirm preliminarily indeed the validity for the cases involving laminar separation bubbles. through 9, Figs. 11 through 14 and Ta- of our method of calculation, particularly
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2012年第6期830-835,共6页
Journal of Northwestern Polytechnical University
基金
国家高技术研究发展计划(2012AA951301)资助
关键词
RANS方程
eN转捩判断方法
线性稳定性理论
边界层转捩
层流分离泡
airfoils, algorithms, boundary conditions, laminar boundary layer, calculations, computer simulation,computer software, flow fields, flowcharting, linear stability analysis, mathematical models, NavierStokes equations, two dimensional, unmanned aerial vehicles （UAV）, stability
boundary layer tran-sition, eN transition prediction method, laminar separation bubble, linear stability theory, Reynolds-Averaged Navier Stokes （RANS） equations
