摘要
采用SIMPLE方法求解GAO-YONG不可压湍流方程组,对不同来流迎角下的NACA0012翼型绕流结构进行了数值模拟,给出了翼型绕流分离流结构随迎角的变化特征和翼型在分离绕流中的气动力参数.与实验数据以及大涡模拟结果的比较表明,GAO-YONG不可压湍流方程组能够对翼型绕流的分离点、分离涡形态、表面压力分布、升阻特性做出较好的预测,能够模拟翼型大攻角分离流动,计算结果优于FLU-ENT软件中的k-ε、k-ω、k-ωsst模型的计算结果.
The NACA0012 isolated airfoil at different angels of attack is numerically simulated with SIMPLE algorithm and GAO-YONG turbulence equations. The problem of checkerboard prediction of pressure was cured by evaluating the cell face velocities by the momentum interpolated principle. In order to improve the calculation precision, an orthogonal body fitted coordinate system was selected and a second-order HLAP discretization for the convective part was used. Separated flow structures over the isolated airfoil at different angles of attack and corresponding aerodynamic parameters are presented in details. By comparing with the experimental data and the results of the large-eddy simulation, it shows the GAO-YONG turbulence equations without using empirical coefficients and wall functions successfully simulate the separated flow pattern on the airfoil surface, and accurately predict the location of separation and the aerodynamic force coefficients. In addition, the results of GAO-YONG turbulence equations are better than that of k-ε,k-ω,k-ω sst turbulence models in the software of FLUENT soft.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第1期73-78,共6页
Journal of Aerospace Power
