摘要

Compressible solutions of Reynolds-averaged Navier-Stokes equations are found for three-dimensional flow past an isolated NACA blades using several turbulence models: two-equation models and Reynolds stress models which are currently being tried out for the computation of flow past airfoils. Numerical results on the behaviour of NACA 0012, NACA 7512 and NACA 6512 at high chord Reynolds number are presented for 0.45 and 0.85 Mach number values. The focus is devoted to the comparison between model results particularly for stall conditions corresponding to separated flow. All the calculations have been performed using CFX 5.7.1^® code. It is found that the Shear Stress Transport (SST) model resolves the passage vortex better on the suction side of the profiles.