Numerical analysis of air flow past the 2415-3S airfoil for an unmanned aerial vehicle with internal propulsion system

Velázquez-Araque, L.; Mendoza Perez, Luis Daniel; Casanova Kindelán, Jesús y Nozicka, J. (2013). Numerical analysis of air flow past the 2415-3S airfoil for an unmanned aerial vehicle with internal propulsion system. En: "ISTP-24. The International Symposium on Transport Phenomena", 1 - 5 November 2013, Yamaguchi, Japan. pp. 1-5.

Descripción

Título: Numerical analysis of air flow past the 2415-3S airfoil for an unmanned aerial vehicle with internal propulsion system
Autor/es:
  • Velázquez-Araque, L.
  • Mendoza Perez, Luis Daniel
  • Casanova Kindelán, Jesús
  • Nozicka, J.
Tipo de Documento: Ponencia en Congreso o Jornada (Artículo)
Título del Evento: ISTP-24. The International Symposium on Transport Phenomena
Fechas del Evento: 1 - 5 November 2013
Lugar del Evento: Yamaguchi, Japan
Título del Libro: ISTP-24. The 24th International Symposium on Transport Phenomena
Título de Revista/Publicación: international journal of aerospace and Ligtweight Structures
Fecha: 2013
Materias:
Escuela: E.T.S.I. Industriales (UPM)
Departamento: Ingeniería Energética
Licencias Creative Commons: Reconocimiento - Sin obra derivada - No comercial

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Resumen

This paper deals with the prediction of pressure and velocity fields on the 2415-3S airfoil which will be used for and 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 tridimensional 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-ε model is utilized to describe the turbulent flow process as followed in references. Results allowed obtaining pressure and 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.

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ID de Registro: 38825
Identificador DC: http://oa.upm.es/38825/
Identificador OAI: oai:oa.upm.es:38825
Depositado por: Memoria Investigacion
Depositado el: 13 Ene 2016 16:39
Ultima Modificación: 25 Ene 2016 17:11
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