Aerodynamic Characteristics of a NACA 0010 Airfoil with Rotating Cylinders

The aerodynamics and flow field characteristics of a NACA 0010 airfoil with rotating cylinders near the leading-edge were investigated in flow with a freestream turbulence intensity of 4%. A NACA 0010 airfoil was modified so that 5 micro-DC motors fit within the airfoil body at 14.6% of chord length from the leading edge. Cylinders with a diameter of 0.75 inches and a width of 0.5 inches were attached to the motor shafts with only 3mm of the cylinders being exposed to the incoming flow. Experiments were carried out on the NACA 0010 airfoil with and without the rotating cylinders. The cylinders were driven by micro-DC motors with 12 volts, which translates to 3400 RPM, with the cylinder rotation being counter-clockwise to the direction of the flow. The Reynolds number varied from 173,400 to 218,900. The angle of attack was varied within the range of 0 to 24 degrees. The forces and torque experienced by the airfoil are measured using two 9105-TIF-DELTA ATI 6-axis force/torque transducers. From the results, it was shown that the airfoil with the cylinders rotating experienced a maximum lift coefficient increase of 45 percent when compared to results from an unmodified baseline airfoil.