Analysis of air flow past and through the 2415-3S airfoil for an unmanned aerial vehicle with internal propulsion system

Velázquez-Araque, L.; Mendoza Pérez, Luis Daniel y Nožička, J. (2014). Analysis of air flow past and through the 2415-3S airfoil for an unmanned aerial vehicle with internal propulsion system. "Journal of Systemics, Cybernetics and Informatics", v. 12 (n. 4); pp. 26-31. ISSN 1690-4524.

Descripción

Título: Analysis of air flow past and through the 2415-3S airfoil for an unmanned aerial vehicle with internal propulsion system
Autor/es:
  • Velázquez-Araque, L.
  • Mendoza Pérez, Luis Daniel
  • Nožička, J.
Tipo de Documento: Artículo
Título de Revista/Publicación: Journal of Systemics, Cybernetics and Informatics
Fecha: 2014
Volumen: 12
Materias:
Escuela: E.T.S.I. Industriales (UPM)
Departamento: Otro
Licencias Creative Commons: Reconocimiento - Sin obra derivada - No comercial

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Resumen

This paper deals with the prediction of velocity fields on the 2415-3S airfoil which will be used for an unmanned aerial vehicle with internal propulsion system and in this way analyze the air flow through an internal duct of the airfoil using computational fluid dynamics. The main objective is to evaluate the effect of the internal air flow past the airfoil and how this affects the aerodynamic performance by means of lift and drag forces. For this purpose, three different designs of the internal duct were studied; starting from the base 2415-3S airfoil developed in previous investigation, basing on the hypothesis of decreasing the flow separation produced when the propulsive airflow merges the external flow, and in this way obtaining the best configuration. For that purpose, an exhaustive study of the mesh sensitivity was performed. It was used a non-structured mesh since the computational domain is three-dimensional and complex. The selected mesh contains approximately 12.5 million elements. Both the computational domain and the numerical solution were made with commercial CAD and CFD software, respectively. Air, incompressible and steady was analyzed. The boundary conditions are in concordance with experimental setup in the AF 6109 wind tunnel. The k-e model is utilized to describe the turbulent flow process as followed in references. Results allowed obtaining velocity contours as well as lift and drag coefficients and also the location of separation and reattachment regions in some cases for zero degrees of angle of attack on the internal and external surfaces of the airfoil. Finally, the selection of the configuration with the best aerodynamic performance was made, selecting the option without curved baffles.

Más información

ID de Registro: 38747
Identificador DC: http://oa.upm.es/38747/
Identificador OAI: oai:oa.upm.es:38747
URL Oficial: http://www.iiisci.org/journal/sci/Home.asp
Depositado por: Memoria Investigacion
Depositado el: 17 Dic 2015 16:04
Ultima Modificación: 18 Dic 2015 07:59
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