Aerodynamic Analysis of Active Trailing-Edge Flaps and Passive Surface Roughness on NACA 4412 Airfoil

The focus of this study is to understand the effect of the flow control mechanism on NACA 4412 airfoil. Two configuration of flow control method is used in this investigation. The first configuration is, airfoil with only the trailing-edge flap. This is the active flow control method. The trailing-edge flap can be deflected to various angle accordingly. The second configuration is a combination of, active trailing-edge flap with a passive surface roughness at the leading-edge of the airfoil. The surface roughness is expected to reduce the flow separation at the leading-edge of the airfoil. This is expected to enhance the aerodynamic performance of the airfoil. Both configuration 1 and configuration 2 was simulated and the results compared with the base airfoil without any flow control mechanism. Based on the results, airfoil with configuration 1 performed better compared to the base airfoil. Airfoil with configuration 2, performed well but not better than the airfoil with configuration 1. Upon further analysis, key patterns emphasise airfoil with configuration 2 could perform better if the roughness element parameters further optimised. This airfoil to be used for wind turbine applications.