Two Dimensional CFD Simulation of Optimizing Lift to Drag Ratio of Flapping Tandem NACA 0012 Airfoils

NACA 0012 airfoil is a symmetrical airfoil that has been widely used in aerodynamic studies. This research investigates the maximum lift to drag ratio (L/D) of the flapping NACA 0012 airfoils under different configurations at low Reynolds numbers (Re 1300). Through Computational Fluid Dynamics (CFD) simulations using COMSOL, the research first optimizes the configuration of a single airfoil with a linear motion and a rotational motion by varying the amplitude of the rotational motion and the phase difference between two motions, and then apply the results on simulations of two tandem airfoils with the same motions, by changing the distance between the airfoils and the phase difference between the linear motion of two airfoils. A maximum lift to drag ratio is reached in each simulation. The studies are significant in understanding the effect of vortex produced by the front airfoil on the rear airfoil, and can guide the design of new airfoil and new energy recovery systems.