This study presents a detailed numerical investigation of the aerodynamic performance of a NACA 0015 airfoil enhanced with a leading-edge rotating cylinder. A parametric analysis was conducted to evaluate the effects of rotational speed (10, 50, 100, 150 and 200 rad/s), cylinder diameter (13 mm, 14 mm and 15 mm), angle of attack (5°, 10°, 15°, 20°, 25° and 30°), and the Reynolds number varies with free-stream velocities of 15, 30, 50, and 100 m/s, with corresponding values of 152,279, 304,558, 507,597, and 1,015,193, respectively on the lift coefficient. A non-dimensional parameter, the cylinder surface velocity to free-stream velocity ratio was introduced to assess its influence on flow characteristics and lift enhancement. Results reveal that higher rotational speeds and larger cylinder diameters significantly increase lift coefficient, particularly at elevated angles of attack, with peak lift occurring between 15° and 20°. Higher Reynolds numbers further amplify aerodynamic efficiency by delaying flow separation. These findings, supported by validated computational simulations and a predictive polynomial model, highlight the leading-edge rotating cylinder potential as an effective active flow control mechanism. This research provides novel insights into optimising airfoil performance for applications in aerospace, unmanned aerial vehicles, and renewable energy systems.
Minglani et al. (Thu,) studied this question.