ABSTRAKT

The prediction of shock induced oscillations over transonic rigid airfoils is important for a better understanding of the buffeting phenomenon. The unsteady resolution of the Navier-Stokes equations is realized with various transport-equation turbulence models in which corrections are added for non-equilibrium flows. The lack of numerical efficiency due to the CFL stability condition is circumvented by the use of a wall law approach and a dual time stepping method. Comparisons are made with experimental results obtained for the supercritical RA16SC1 airfoil. They show the interest of the use of the SST correction or realizability conditions to get correct predictions of the frequency, the amplitude and the pressure fluctuations over the airfoil.