Determinação experimental dos coeficientes de arrasto e sustentação do perfil de asa NACA 0018
This article presents the experimental analysis of the NACA 0018 airfoil, aiming to determine the lift and drag coefficients at various angles of attack. The NACA 0018 airfoil, characterized by its symmetry, was evaluated for aerodynamic performance and behavior under critical conditions, such as th...
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| Tipo de recurso: | artículo |
| Estado: | Versión publicada |
| Fecha de publicación: | 2024 |
| País: | Brasil |
| Institución: | Pontifícia Universidade Católica do Rio Grande do Sul (PUCRS) |
| Repositorio: | Repositório Institucional PUCRS |
| Idioma: | portugués |
| OAI Identifier: | oai:meriva.pucrs.br:10923/27016 |
| Acceso en línea: | https://hdl.handle.net/10923/27016 |
| Access Level: | acceso abierto |
| Palabra clave: | AERODINÂMICA PERFIL NACA 0018 COEFICIENTE DE SUSTENTAÇÃO COEFICIENTE DE ARRASTO TÚNEL DE VENTO PERFIL DE ASA AERODYNAMICS NACA 0018 AIRFOIL LIFT COEFFICIENT DRAG COEFFICIENT WIND TUNNEL WING PROFILE |
| Sumario: | This article presents the experimental analysis of the NACA 0018 airfoil, aiming to determine the lift and drag coefficients at various angles of attack. The NACA 0018 airfoil, characterized by its symmetry, was evaluated for aerodynamic performance and behavior under critical conditions, such as the proximity to stall. Stall occurs when the angle of attack exceeds the critical limit, leading to the separation of airflow from the airfoil surface, resulting in a drastic reduction in lift. During the experiments, it was observed that the airfoil achieved maximum efficiency around 10º, with a significant increase in drag and the onset of stall at higher angles. Comparisons with theoretical data revealed discrepancies attributed to experimental conditions, emphasizing the importance of validating theoretical models under real-world scenarios. |
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