Aerodynamic Flow Control Using Micro Rotating Cylinders

This research investigates the aerodynamic and flow field characteristics of a NACA 0010 airfoil equipped with rotating cylinders near the leading edge, subjected to a flow with a freestream turbulence intensity of 4.3%. The airfoil was modified to integrate five micro-DC motors positioned at 14.5% of the chord length from the leading edge. The cylinders, with dimensions of 0.75 inches in diameter and 0.5 inches in width, exposed 3mm of their length to the incoming flow. A modified leading edge with eight sinusoidal protrusions (tubercles) was employed to compare the performance of the micro-rotating cylinder airfoil with an unmodified baseline airfoil. Experimental investigations were conducted on the NACA 0010 airfoil with and without the rotating cylinders, driven by a 12-volt power supply with a counter-clockwise rotation at 3000 RPM. The experiments encompassed a Reynolds number range of 138,400 to 412,200 and variations in the angle of attack from 0 to 24 degrees. Force and torque measurements were obtained using two 6-axis force/torque transducers. The experimental findings revealed a significant increase in the maximum lift coefficient for the airfoil equipped with rotating cylinders, demonstrating a 45% enhancement compared to the unmodified baseline airfoil