Large eddy simulation of flow Separation Control over a NACA 2415 airfoil

This study involves numerical simulation of the flow around a NACA2415 airfoil, with a 15°angle of attack, and flow separation control using a rod, It involves putting a cylindrical rod in the upstream of the leading edge in order to accelerate the transition of the boundary layer by interaction between the wake behind the rod and the boundary layer. The viscous, non-stationary flow is simulated using ANSYS FLUENT 13. Our results show a substantial modification in the flow structure and a maximum drag reduction of 51%.