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Please use this identifier to cite or link to this item: https://dspace.lboro.ac.uk/2134/10067

Title: The influence of hole orientation on the aerodynamics of battle damaged wings
Authors: Render, Peter M.
Pickhaver, T.W.
Keywords: Battle damage
Wing aerodynamics
Issue Date: 2012
Publisher: © Peter Render. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.
Citation: RENDER, P.M. and PICKHAVER, T.W., 2012. The influence of hole orientation on the aerodynamics of battle damaged wings. IN: Proceedings of the 30th AIAA Applied Aerodynamics Conference, New Orleans, USA, Paper AIAA 2012-2890, 14 pp.
Abstract: Wind tunnel tests were carried out on an NASA LS(1)-0417MOD aerofoil with a circular hole simulating gunfire damage. To represent different attack directions, the inclination of the hole axis relative to the aerofoil chord was varied. The hole had a diameter of 20% of the aerofoil chord and its axis was centred at half chord. The aerofoil spanned the wind tunnel to create approximate two-dimensional conditions and balance measurements were carried out at a Reynolds number of 500, 000. Surface flow visualisation and pressure measurements were also carried out. The aerofoil model incorporated a cavity to represent the internal geometry of an aircraft’s wing. Compared to an undamaged wing the addition of damage increased drag, reduced lift and gave a more negative pitching moment. The effects increased with incidence. Adding negative obliquity, where the upper surface hole was moved forward and the lower hole rearwards, increased the magnitude of these effects. Except when combined with extreme negative obliquity, adding skew, where the holes were offset in a spanwise direction, had little measurable effect in terms of aerodynamic coefficients. However, adding skew introduced asymmetry to the flow through the damage.
Description: This conference paper was presented at the 30th AIAA Applied Aerodynamics Conference, 25 - 28 June 2012, New Orleans, Louisiana, USA. The AIAA website is at: https://www.aiaa.org/
Version: Published
URI: https://dspace.lboro.ac.uk/2134/10067
Appears in Collections:Conference Papers and Contributions (Aeronautical and Automotive Engineering)

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