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ISSN: 1546-9239 (Print)
ISSN: 1554-3641 (Online)
Research Article Open Access

An Investigation of the Effect of Aspect Ratio on the Airfoil Performance

M. Kopaç1, M. Yılmaz1 and T. Gültop2
  • 1 Department of Mechanical Engineering, Karaelmas University, Zonguldak, Turkey
  • 2 Department of Civil Engineering, Gazi University, Ankara, Turkey

Abstract

The effect of aspect ratio on the airfoil performance is investigated for airflow about axially symetric wings as a function of the angle of attack. The magnitudes of aerodynamic forces and moments on airfoils resulting from the incompressible viscous flow fields are determined experimentally. The TE54 wind tunnel used for the experiments is an open conduit and has a 300x300 mm x-section with a closed test chamber. The TE81 digital measurement device is used which has three components. Three different types of airfoil profiles are tested under the airflow speed of 33.76 m s-1 and it is concluded that the airfoil with the aspect ratio of 2.761 yields the optimum performance.

American Journal of Applied Sciences
Volume 2 No. 2, 2005, 545-549

DOI: https://doi.org/10.3844/ajassp.2005.545.549

Submitted On: 10 April 2006 Published On: 28 February 2005

How to Cite: Kopaç, M., Yılmaz, M. & Gültop, T. (2005). An Investigation of the Effect of Aspect Ratio on the Airfoil Performance. American Journal of Applied Sciences, 2(2), 545-549. https://doi.org/10.3844/ajassp.2005.545.549

Open AccessCopyright: © 2005 M. Kopaç, M. Yılmaz and T. Gültop. This is an open access article distributed under the terms of the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original author and source are credited.

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Keywords

  • Airfoil
  • Drag Coefficient
  • Air Flow
  • Airfoil Performance