Aerodynamic Performance of NACA 662-015 Airfoil with Gurney Flap
A numerical simulation was executed by using of ANSYS Fluent to demonstrate the effect of a Gurney flap (GF) on a National Advisory Committee for Aeronautics (NACA) 662-015 airfoil. The GFs are remarkable aerodynamic elements that show how a small modification to an airfoil’s trailing edge can have...
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| Main Authors: | , , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Instituto de Aeronáutica e Espaço (IAE)
2024-12-01
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| Series: | Journal of Aerospace Technology and Management |
| Subjects: | |
| Online Access: | https://jatm.com.br/jatm/article/view/1347 |
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| Summary: | A numerical simulation was executed by using of ANSYS Fluent to demonstrate the effect of a Gurney flap (GF) on a National Advisory Committee for Aeronautics (NACA) 662-015 airfoil. The GFs are remarkable aerodynamic elements that show how a small modification to an airfoil’s trailing edge can have a significant impact on performance, making them a valuable tool in the pursuit of enhanced efficiency and control in various applications with increased downforce and minimal drag penalty. The height of the flap was varied from 1% of the chord up to 3% of the chord of the airfoil, with 0.5% incremental steps. The increase in lift obtained and the subsequent penalty of increased drag were quantified in terms of percentage increase compared to the clean airfoil. As a result, the lift-to-drag ratio was found to be a net positive, with the most significant increase at a 2.5% GF height-to-chord ratio. Along with the lift augmentation, the impact of the GF on the zero-lift angle of attack, lift slope, and stall angle was investigated. Furthermore the alteration of the Kutta condition as a result of installing the GF on the airfoil. The improved aerodynamic effectiveness of airfoils using GFs is mostly observed in the motorsports and aviation sectors.
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| ISSN: | 2175-9146 |