Akademik Veri Yönetim Sistemi
6. Uluslararası Boğaziçi Bilimsel Araştırmalar Kongresi, İstanbul, Türkiye, 18 - 19 Ocak 2025, cilt.1, sa.1, ss.628-647, (Tam Metin Bildiri)
This study investigates the aerodynamic performance and vibration characteristics of NACA0021 airfoil under different angles of attack. Respectively, the following angles were analyzed: 0°, 5°, 10°, 15°, 20°, 25°, 30°, 40°, 50°, 60°. Three different airfoils, which are a baseline airfoil, an airfoil with a mid-chord micro spoiler, and an airfoil with quarter-chord micro spoiler were analyzed under Reynolds number of 1E6. Lift and drag coefficients were calculated for each airfoil under each of those specified angles of attack to assess the aerodynamic performance of the airfoils. A mesh independence analysis was employed to ensure the accuracy of the airfoils' aerodynamic performance.
The results show that the baseline airfoil experiences stall at an angle of attack of around 15°, while airfoils with micro spoilers reach the stall at an angle of attack of around 20°. Featuring a micro spoiler on airfoils enhance aerodynamic performance by delaying stall through a reduction of flow separation. To obtain the structural response of airfoils, two-way FSI simulations were performed using the intrinsic FSI solver available in ANSYS FLUENT. This solver allows for the coupling of the fluid and structural domains. Airfoils’ tip displacement measurements from the simulations were demonstrated, and the effectiveness of micro spoilers was explored.