中文摘要：

采用不同湍流模型,对NACA0012翼型,在不同迎角和不同高马赫数下的绕流流场进行数值模拟;通过与风洞实验对比,评估了S-A模型,Realizable k-ε模型和κ-ωSST模型对高雷诺数绕流流场数值模拟的准确性;并运用Realizable k-ε模型精确模拟并分析了二维翼型绕流流场的跨音速特性,为理论分析及工程设计提供参考.

英文摘要：

Numerical simulations of the flows around the NACAO012 airfoil, with different angles of attack and different Mach number, using different turbulence models were presented and compared with experimental data. Three turbulent models, including S-Amodel, Realizable k-8 model and k-to SST model, were comparable in their agreement with experiment for high Reynolds number. Realizable k-6 model was used to accurately simulate the characteristics of transonic flows around two-dimensional airfoil, which provides a reference for the theoretical anal- ysis and engineering design.