Numerical study of the effect of suction at a compressible and high Reynolds number flow to control the flow separation over Naca 2415 airfoil

Abstract

This study focused on delaying and controlling the flow separation over Naca 2415 airfoil by finding the best slot location with the most effective suction velocity ratio and suction angle to apply suction at a compressible and high Reynolds number flow using computational fluid dynamics method. The results were obtained with two dimensional compressible Reynold-averaged Navier-Stokes equations, and the turbulence was simulated with k-e RNG turbulence model. The results indicated that the most effective slot locations for applying suction were between 0.3 to 0.6 of the airfoil chord length. Also, it was found that the maximum value of the lift coefficient was obtained at an angle of attack of 16° on 0.3 of airfoil chord length and suction velocity ratio of 1.5. This value is about 55% compared to the case without suction, and thus the stall angle increased from 10° to 16°.