Numerical analysis on the effect of rotating cylinder over the symmetrical airfoil.

Even though symmetrical airfoil has less lift-drag ratio and the undesirable stall characteristics it has been used in the rotary wing applications. Increasing the aerodynamics efficiency by using the different flow control methods are the important research in recent years. Amplifying the lift coefficient without causing any negative impact on the drag coefficient will create the great impact on aeronautical domain. Hence this paper objective is by using cylinder rotation- an active flow control method to improve the aerodynamic efficiency over the airfoil. To get the optimum values of lift and drag coefficient the flow parameters, velocity ratios of the cylinder Vc / V∞ and the location of the cylinder have been used. The model of the NACA 0012 airfoil with cylinder is developed by using Inventor and the numerical analysis were carried out by using Ansys fluent. Analysis was carried out for the velocity ratios of 0.5,1 and 2 by placing the cylinder at the chordwise locations of 10% to 50% of its length. When compared the results of NACA 0012 airfoil with cylinder and without cylinder there is a significant growth in aerodynamic efficiency and delayed in stall angle. Generally, the performance was increase in the ratio of cylinder rotation speed Vc to the freestream speed V∞. There appears to be an optimal location for the rotating cylinder which gave quite promising results. [ABSTRACT FROM AUTHOR]