The Effect of Location and Shape of Vortex Generators on Aerodynamic Characteristics of a NACA 4415 Airfoil
This study examines the flow behavior and lift coefficient variations of a NACA 4415 airfoil using different vortex generator configurations. Experimental investigations are conducted in a subsonic wind tunnel at a Reynolds number of 1.8 x 105. The airfoil is tested with two types of vortex generat...
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| Format: | Article |
| Language: | English |
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Al-Nahrain Journal for Engineering Sciences
2023-10-01
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| Series: | مجلة النهرين للعلوم الهندسية |
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| Online Access: | https://nahje.com/index.php/main/article/view/1069 |
| _version_ | 1827777526419685376 |
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| author | Khuder N. Abed |
| author_facet | Khuder N. Abed |
| author_sort | Khuder N. Abed |
| collection | DOAJ |
| description |
This study examines the flow behavior and lift coefficient variations of a NACA 4415 airfoil using different vortex generator configurations. Experimental investigations are conducted in a subsonic wind tunnel at a Reynolds number of 1.8 x 105. The airfoil is tested with two types of vortex generators, namely the dome vortex and the convergent-divergent vortex, positioned at 10%, 28%, and 60% chord locations. Experimental lift coefficients are compared with Airfoil Tools database, showing consistent agreement within an angle of attack range of 0 to 18 degrees. At small angles of attack (0 to 8 degrees), the lift coefficients of the NACA 4415 airfoil with the dome vortex at 10%, 28%, and 60% chord positions are lower compared to the baseline configuration. However, beyond 14 degrees, the highest lift coefficient value after the angle range of 14-18 degrees is achieved at the 60% chord position with the dome vortex, 10.43% increase compared to the baseline lift coefficient. Furthermore, the best value for the lift coefficient after the angle range of 16-18 degrees at the 10% chord position is achieved with the dome vortex, where the maximum lift coefficient 9.4% increase compared to the baseline lift coefficient. It is noted that the baseline configuration consistently outperforms the convergent-divergent vortex configurations.
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| first_indexed | 2024-03-11T14:20:29Z |
| format | Article |
| id | doaj.art-855fd5f0982b46d6be59271f966ad112 |
| institution | Directory Open Access Journal |
| issn | 2521-9154 2521-9162 |
| language | English |
| last_indexed | 2024-03-11T14:20:29Z |
| publishDate | 2023-10-01 |
| publisher | Al-Nahrain Journal for Engineering Sciences |
| record_format | Article |
| series | مجلة النهرين للعلوم الهندسية |
| spelling | doaj.art-855fd5f0982b46d6be59271f966ad1122023-10-31T17:34:11ZengAl-Nahrain Journal for Engineering Sciencesمجلة النهرين للعلوم الهندسية2521-91542521-91622023-10-0126310.29194/NJES.26030198The Effect of Location and Shape of Vortex Generators on Aerodynamic Characteristics of a NACA 4415 AirfoilKhuder N. Abed0Mechanical Eng. Dept., Diyala University – Baqubah City, Diyala, Iraq This study examines the flow behavior and lift coefficient variations of a NACA 4415 airfoil using different vortex generator configurations. Experimental investigations are conducted in a subsonic wind tunnel at a Reynolds number of 1.8 x 105. The airfoil is tested with two types of vortex generators, namely the dome vortex and the convergent-divergent vortex, positioned at 10%, 28%, and 60% chord locations. Experimental lift coefficients are compared with Airfoil Tools database, showing consistent agreement within an angle of attack range of 0 to 18 degrees. At small angles of attack (0 to 8 degrees), the lift coefficients of the NACA 4415 airfoil with the dome vortex at 10%, 28%, and 60% chord positions are lower compared to the baseline configuration. However, beyond 14 degrees, the highest lift coefficient value after the angle range of 14-18 degrees is achieved at the 60% chord position with the dome vortex, 10.43% increase compared to the baseline lift coefficient. Furthermore, the best value for the lift coefficient after the angle range of 16-18 degrees at the 10% chord position is achieved with the dome vortex, where the maximum lift coefficient 9.4% increase compared to the baseline lift coefficient. It is noted that the baseline configuration consistently outperforms the convergent-divergent vortex configurations. https://nahje.com/index.php/main/article/view/1069Aerodynamic CharacteristicsNACA 4415 AirfoilVortex GeneratorsLift Coefficient |
| spellingShingle | Khuder N. Abed The Effect of Location and Shape of Vortex Generators on Aerodynamic Characteristics of a NACA 4415 Airfoil مجلة النهرين للعلوم الهندسية Aerodynamic Characteristics NACA 4415 Airfoil Vortex Generators Lift Coefficient |
| title | The Effect of Location and Shape of Vortex Generators on Aerodynamic Characteristics of a NACA 4415 Airfoil |
| title_full | The Effect of Location and Shape of Vortex Generators on Aerodynamic Characteristics of a NACA 4415 Airfoil |
| title_fullStr | The Effect of Location and Shape of Vortex Generators on Aerodynamic Characteristics of a NACA 4415 Airfoil |
| title_full_unstemmed | The Effect of Location and Shape of Vortex Generators on Aerodynamic Characteristics of a NACA 4415 Airfoil |
| title_short | The Effect of Location and Shape of Vortex Generators on Aerodynamic Characteristics of a NACA 4415 Airfoil |
| title_sort | effect of location and shape of vortex generators on aerodynamic characteristics of a naca 4415 airfoil |
| topic | Aerodynamic Characteristics NACA 4415 Airfoil Vortex Generators Lift Coefficient |
| url | https://nahje.com/index.php/main/article/view/1069 |
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