A Parametric Study for Passive Control of Shock-Boundary Layer Interaction of an Airfoil with Porous Media in a Transonic Flow

Shock formation due to flow compressibility and its interaction with boundary layer has inappropriate effects, such as drag increase and flow separation. Many methods have been proposed for reduction of these effects, such as vortex generator, suction, and blowing. This paper numerically studies the problem of flow control for NACA0012 airfoil with porous media at transonic flow. Porous media, which combines blowing and suctionm reduces these inappropriate effects. The effects of porous media depth, length, porosity, cell diameter, and angle of attack are investigated in this study. The numerical method is finite volume and the equations are Navier-Stokes. The flow is assumed to be turbulent and stationary. The Results show that the normal shock intensity is weak and consequently the drag coefficient decreases 20 percent. The weakened shock is moved upstream and top of the porous surface region and the shock Mach number is decreased 10 percent. This passive method also postpones the separation point from 58 to 72 percent of the airfoil chord. The efficiency of this method depends on various factors, like geometric parameters.