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

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

Description

Title: Numerical analysis of air flow past the 2415-3S airfoil for an unmanned aerial vehicle with internal propulsion system
Author/s:
  • Velázquez-Araque, L.
  • Mendoza Perez, Luis Daniel
  • Casanova Kindelán, Jesús
  • Nozicka, J.
Item Type: Presentation at Congress or Conference (Article)
Event Title: ISTP-24. The International Symposium on Transport Phenomena
Event Dates: 1 - 5 November 2013
Event Location: Yamaguchi, Japan
Title of Book: ISTP-24. The 24th International Symposium on Transport Phenomena
Título de Revista/Publicación: international journal of aerospace and Ligtweight Structures
Date: 2013
ISSN: 2010-4286
Subjects:
Faculty: E.T.S.I. Industriales (UPM)
Department: Ingeniería Energética
Creative Commons Licenses: Recognition - No derivative works - Non commercial

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Abstract

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.

More information

Item ID: 38825
DC Identifier: http://oa.upm.es/38825/
OAI Identifier: oai:oa.upm.es:38825
Deposited by: Memoria Investigacion
Deposited on: 13 Jan 2016 16:39
Last Modified: 25 Jan 2016 17:11
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