The results of computational and experimental studies of the flow around a symmetric airfoil with a relative thickness of 12% in the free stream and in a low-velocity wind tunnel with a closed test section are presented. The experiments are performed for the Reynolds number Re_c = 0.7·10⁶−2·10⁷ and angles of attack a = −12°÷12°. The problem is numerically solved in a 2D formulation by using the ANSYS Fluent software package. The mathematical model of the flow includes steady Reynolds equations closed by different turbulence models, including the k-ω SST model, which is a superposition of the k-ε and k-ω models. A significant effect of blockage of the wind tunnel test section with limited dimensions by the airfoil on the flow character and aerodynamic characteristics of the airfoil even if the blockage coefficient is only 5.7% is demonstrated.

给出了在自由流中以及在具有封闭测试段的低速风洞中对称翼型周围的相对厚度为12％的流动的计算和实验研究结果。针对雷诺数Re _c = 0.7·10 ⁶ -2·10 ⁷以及迎角α = -12°÷12°进行实验。通过使用ANSYS Fluent软件包，可以在二维公式中以数字方式解决该问题。流动的数学模型包括由不同湍流模型（包括k- ωSST模型）关闭的稳态雷诺方程，其中k- ωSST模型是k-ε和k-ω的叠加楷模。即使阻塞系数仅为5.7％，也显示出翼型有限尺寸的风洞试验段对翼型的流动特性和空气动力特性的显着影响。