The SG 6043 Airfoil Optimization for Low Reynolds Number Applications in Wind Turbines

At first, 71 airfoils, including some symmetrical National Advisory Committee for Aeronautics (NACA) 4-digit, NACA 4-digit, NACA 5-digit, Eppler series, Selig series and other airfoils with higher aerodynamic performance at Reynolds numbers (Re) of 100000 to 600000, the operation range for small wind turbine (SWT) were chosen and analyzed in XFOIL software to determine their lift-to-drag ratio (C_L⁄C_D ). The results showed that the SG6043 airfoil had the highest maximum C_L⁄C_D when compared to the other airfoils. To investigate and enhance the shape modification of the airfoil utilizing variations in thickness-to-camber ratio (t/c) and to determine the ideal t/c at Re of 100,000 to 600,000, the SG6043 airfoil was used. Based on the findings, 0.5 to 1.5 was the optimum t/c at Re of 100,000 to 600,000 for the development of the SG6043 airfoil, which had the maximum〖 C〗_L⁄C_D . Then, three airfoils with varying thicknesses and cambers were designed and analyzed at the mentioned Re, with the optimal t/c being between 0.5 to 1.5. The findings indicated that when the Re increased, SG6043 modified airfoil’s aerodynamic efficiency enhanced. SG6043 modified 1 airfoil presented the greatest〖 C〗_L⁄C_D of 184.85 at a Re of 600000. For the SG6043 modified 2 airfoil, the maximum stall angle (AoA_stall) of 13° was demonstrated for Re of 300000 to 600000. Maximum 〖 C〗_L⁄C_D values for SG6043 modified 1, SG6043 modified 3, and SG6043 modified 2 were 184.85, 182.36, and 177.25, respectively. SG6043 modified 2, SG6043 modified 1, and SG6043 modified 3 had peak lift coefficients (C_L) of 1.798, 1.79, and 1.788, respectively. SG6043 modified airfoils performed well in the drag bucket when initial lift increases were accompanied by either steady or decreasing drag.