Estudio Aerodinámico de Perfiles con Espesor con el Método de Red de Vórtices
In this effort, a numerical study is presented regarding the aerodynamic characteristics of wing sections through the vortex lattice method (VLM). The developed computational implementation allows one to simulate steady-state, quasi-steady and unsteady two- dimensional problems. In this article,...
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| Autores principales: | , , |
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| Formato: | Artículo revista |
| Lenguaje: | Español |
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Facultad de Ciencias Exactas, Físicas y Naturales
2021
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| Acceso en línea: | https://revistas.unc.edu.ar/index.php/FCEFyN/article/view/32320 |
| Aporte de: |
| Sumario: | In this effort, a numerical study is presented regarding the aerodynamic characteristics of wing sections through the vortex lattice method (VLM). The developed computational implementation allows one to simulate steady-state, quasi-steady and unsteady two- dimensional problems. In this article, the estimation error of the computational tool is quantified in terms of the geometry of the wing section: thickness and curvature of the mean line (camber), and of the discretization. It is observed that for the NACA profiles, the error of the estimation of the lift slope increases when the thickness increases but remains bounded between 5 % and 20 % for thicknesses up to 12%. Regarding the camber, the error of the estimation of the lift at zero angle of attack increases with increasing camber and can reach values up to 50%. Finally, for the profile DU97W300, the numerical tool shows a lot of potential since it can predict with high precision the experimental pressure distribution for relatively low angles of attack and also estimates the lift slope and lift for zero angle of attack with an error less than 10%.
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