2 research outputs found
Aerodynamic Study of a Two Groove on the Upper Surface of an Airfoil at Low Angles of Attack
No full textThis study investigates the aerodynamic effects of introducing two semicircular grooves on the upper surface of a NACA 0012 airfoil at low angles of attack using computational fluid dynamics (CFD). The purpose of this research is to evaluate how groove geometry, depth, and spacing influence the lift and drag characteristics and to determine the optimal groove configuration that enhances aerodynamic performance. ANSYS Fluent was utilized to simulate the airflow over a baseline smooth airfoil and modified versions featuring grooves of varying sizes and positions. A grid independence test was conducted to ensure the accuracy and numerical reliability of the simulation. The baseline airfoil simulation was validated against experimental data, showing good agreement with a maximum relative error of less than 10%. The results revealed that a single groove of 0.01c depth provided an increase in lift and a notable drag reduction, particularly at a 10° angle of attack. Further investigations with two grooves, where the first groove was fixed at 0.25c and the second varied between 0.239c and 0.45c, showed that the optimal configuration was with the second groove placed at 0.35c. The study concludes that proper groove positioning and sizing can effectively delay flow separation, enhance lift, and reduce drag in low-speed aerodynamic applications. These findings suggest potential benefits for UAVs, gliders, and other airfoil-based systems operating at low angles of attack
Aerodynamic Study of a Single Groove on The Upper and Lower Surfaces of an Airfoil at Low Angles of Attack
No full textThis project investigates the aerodynamic effects of introducing a single groove on both the upper and lower surfaces of a NACA 0012 airfoil at low angles of attack, ranging from 0° to 10°. Each simulation features two grooves, one on the upper surface and one on the lower surface, to evaluate their combined influence on lift and drag performance. The objective is to determine whether passive flow control via surface grooves can enhance aerodynamic efficiency in low-speed conditions. The study was conducted using computational fluid dynamics (CFD) simulations in ANSYS Fluent. Several groove configurations were analyzed, including parallel grooves at 0.20C, 0.25C, and 0.30C, as well as fixed upper grooves at 0.25C and 0.30C combined with variable lower groove positions at 0.25C to 0.40C. A mesh independence test and validation against experimental data were performed to ensure simulation accuracy. A groove diameter of 1.0 cm was selected based on its favorable aerodynamic performance across the tested angles of attack. Results indicate that the configuration with a fixed upper groove at 0.25C and a lower groove at 0.40C yields the most significant lift improvement and slight drag reduction compared to the baseline airfoil. The study demonstrates that using two grooves in a dual-surface configuration can effectively delay flow separation and enhance the lift-to-drag ratio. These findings support the advancement of passive aerodynamic control strategies in low-speed airfoil applications
