Numerical investigation of impressible turbulent flows past airfoils

The standard k-ω model and the k-ω model coupled with dispersion model were computed for turbulent flow over two airfoils, NACA 0012 and NACA 4412. The flow characteristics on the surface of the NACA 0012 airfoil were analyzed in detail under a typical Reynolds number of 2.88×10⁶ and attack angle from 0° to 15° including pressure coefficient, lift coefficient and drag coefficient; the flow characteristics on the surface of the NACA 4412 airfoil were analyzed in detail under a typical Reynolds number of 1.52×10⁶ and attack angle of 13.87° including the flow separation and pressure coefficient, and then compared with the experiment data. Under the same condition, the new model improved the accuracy of about 5% than the standard k-ω model when calculating the lift coefficient of NACA 0012, and improved the accuracy of about 3% than the standard k-ω model when calculating the pressure coefficient of NACA 4412. The results prove its credibility and value further more.