Author

# Mohsen Seifi Davari

Bio: Mohsen Seifi Davari is an academic researcher. The author has contributed to research in topics: Vertical axis wind turbine & Vertical axis. The author has an hindex of 1, co-authored 1 publications receiving 1 citations.

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21 Mar 2023

TL;DR: In this article , a wind turbine schematics was designed in Catia software and the height of the blades was 35 and 75 centimeters, the radius of the blade was 18.5 cm and the length of the airfoil 6.4 Cm is.

Abstract: Three airfoils NACA0015, NACA0018 and NACA0021 were selected and in the Q-Blade software, the coefficients of shear, post and the maximum ratio of the exponential coefficients were determined and, finally, the Airfoil Nakata 0015 at a speed of 5 and 10 meters per second, was selected and best. Fluent software was used to solve it, based on the finite volume method. For numerical analysis, the turbulence method K-ω SST was validated with experimental results. The wind turbine schematics was designed in Catia software and the height of the blades was 35 and 75 centimeters, the radius of the blade was 18.5 cm and the length of the airfoil 6.4 Cm is. The results show that in order to operate the turbine of porous blade windings at 35 cm height at speeds of 1, 2, 3, 4, 5, 7, 7.45, 8.25, 8.5 m / s 50% 50%, 33%, 50%, 50%, 60%, 57%, 55%, 50%, and for setting up a porous blade wind turbine at a height of 75 cm at a speed of one, two, three, four, Five, seven, 7.45, 8.25, 8.5, 9, 9.5 m / s 66.6%, 75%, 80%, 71.4%, 66.6%, 76.9%, 80%, 82%, 89%, 100% of the launching force Smooth wind turbine is required at the same height.

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TL;DR: In order to select an airfoil suitable for the wind tunnel testing on a three-bladed Darrieus H-rotor wind turbine, several symmetrical National Advisory Committee for Aeronautics (NACA) 4-digit, NACA 5-digit and Selig airfoils with chord Reynolds numbers of 17,890, 35,780, and 53,670 were studied as discussed by the authors .

Abstract: In order to select an airfoil suitable for the wind tunnel testing on a three-bladed Darrieus H-rotor wind turbine, several symmetrical National Advisory Committee for Aeronautics (NACA) 4-digit, NACA 4-digit, NACA 5-digit, and Selig airfoils with chord Reynolds numbers (Rec) of 17,890, 35,780, and 53,670 were studied. To achieve higher aerodynamic performance at Re of 17,890 to 53,670, the NACA0015 airfoil was selected. The lift coefficient (Rec) of the NACA0015 airfoil after shape modification has reached values of 0.788 to 0.936 at Re of 35,780 and 0.925 to 1.027 at Re of 53,670 with the same stall angle (AoAstall) in both investigated Re, according to the results of modifying the airfoil’s thickness and chord. Additionally, the NACA0015 modified airfoil’s maximum lift-to-drag ratio coefficient (CL/CD) increased by 34.01% and 17.94% at Re of 35780 and 53,670, respectively. Likewise, the analysis showed that the NACA0015 modified airfoil’s maximum performance coefficient (CP) increased from 0.129, 0.242, 0.285, 0.308, and 0.33 to 0.152, 0.272, 0.307, 0.331, and 0.354 at Re of 100,000, 150000, 200000, 250000, and 300,000, respectively. As well as the findings demonstrated that the XFOIL code provides the most accurate overall prediction results at low Re.