Numerical research on a drag reduction technique used for the NACA 0012 airfoil

Abstract

The objective of this study is to propose a new method of drag reduction applied to a NACA 0012 aerodynamic airfoil. A device has been installed at a point in the area where flow separation is likely to occur. It allows reducing drag of the airfoil. The numerical simulations have been carried out in the two−dimensional case. The computational fluid dynamics (CFD) software Ansys Fluent 17.0 has been used. An incompressible and laminar flow has been considered for a Reynolds number of Re = 1000. An angle of attack of 5° has been considered. Results show that in certain device configurations, drag could be reduced while the lift−to−drag ratio increases. Future works concern studying this drag reduction device for other angles of attack.

Drag Reduction of a NACA Aerodynamic Airfoil: A Numerical Study

“…This study aims to minimize drag experienced by the NACA 0012 airfoil through innovative techniques [11]. To achieve this goal, a device is strategically positioned at the separation point on the airfoil, enabling efficient separation control and subsequent drag reduction.…”