The SG6043 airfoil optimization for low Reynolds number applications in wind turbines

Hossein Seifi  Davari; Mohammad Yaghoub Abdollahzadeh  Jamalabadi; Mohsen Seify  Davari

doi:10.59400/mea2486

The SG6043 airfoil optimization for low Reynolds number applications in wind turbines

Hossein Seifi Davari Ocean Engineering Department, Chabahar Maritime University, Chabahar 99717, Iran
Mohammad Yaghoub Abdollahzadeh Jamalabadi Ocean Engineering Department, Chabahar Maritime University, Chabahar 99717, Iran
Mohsen Seify Davari Germi Department, Islamic Azad University, Germi 56911, Iran

Article ID: 2486

DOI: https://doi.org/10.59400/mea2486

Keywords: modified airfoil; Reynolds numbers; aerodynamic; lift-to-drag; optimization; XFOIL software

Abstract

This study focuses on optimizing the SG6043 airfoil for small wind turbines (SWTs) operating at low Reynolds numbers (Re = 100,000 to 600,000). Using XFOIL software, 71 airfoils were analyzed, and the SG6043 airfoil demonstrated the highest lift-to-drag ratio (C_L/C_D). Three modified airfoils were designed by varying the thickness-to-camber ratio (t/c) between 0.5 and 1.5. The SG6043 modified 1 airfoil achieved a maximum C_L/C_D of 184.85 at Re = 600,000, outperforming other airfoils. These findings provide valuable insights for designing more efficient SWTs for low wind speed applications. At first, 71 airfoils, including some symmetrical National Advisory Committee for Aeronautics (NACA) 4-digit, NACA 5-digit, Eppler series, Selig series, and other airfoils with higher aerodynamic performance at Reynolds numbers (Re) of 100,000 to 600,000 (the operation range for small wind turbines, SWTs), 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 and 1.5. The findings indicated that when the Re increased, the 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 600,000. For the SG6043 modified 2 airfoil, the maximum stall angle (AoA_stall) of 13° was demonstrated for Re of 300,000 to 600,000. 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.

Published

2025-04-08

How to Cite

Davari, H. S., Jamalabadi, M. Y. A., & Davari, M. S. (2025). The SG6043 airfoil optimization for low Reynolds number applications in wind turbines. Mechanical Engineering Advances, 3(2), 2486. https://doi.org/10.59400/mea2486

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Issue

Vol. 3 No. 2 (2025)

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Article

This work is licensed under a Creative Commons Attribution 4.0 International License.

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