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Aerodynamics of battle-damaged finite-aspect-ratio wings

journal contribution
posted on 18.01.2010, 12:02 authored by Peter M. Render, Mujahid Samad-Suhaeb, Zhiyin Yang, Mahmoud Mani
Wind-tunnel tests have been carried out on a battle-damaged NACA 641–412 half-wing aspect ratio of 8.2. The simulated gunfire damage had a diameter of 0.2 wing chord and was located at midchord and at one of two spanwise locations. Tests were carried out at a Reynolds number of 5:5 105. Compared with an undamaged wing, the damage resulted in reduced lift, increased drag and a positive increase in pitching moment at zero lift. Moving the damage to near the tip reduced the magnitude of these effects. Using the static pressure difference between the upper and lower surfaces of the undamaged wing allowed the data from the present study to be successfully compared with previously published drag and lift data for a two-dimensional damaged airfoil. Tests on wings with aspect ratios of 6.2 and 10.3 produced similar trends in the aerodynamic characteristics and showed that the use of static pressure difference was equally effective in allowing comparisons with two-dimensional data.

History

School

  • Aeronautical, Automotive, Chemical and Materials Engineering

Department

  • Aeronautical and Automotive Engineering

Citation

RENDER, P.M. ... et al, 2009. Aerodynamics of battle-damaged finite-aspect-ratio wings. Journal of Aircraft, 46 (3), pp. 997-1004.

Publisher

© American Institute of Aeronautics and Astronautics (AIAA)

Version

NA (Not Applicable or Unknown)

Publication date

2009

Notes

This article is closed access. It was published in the Journal of Aircraft [© American Institute of Aeronautics and Astronautics] and is available from: http://dx.doi.org/10.2514/1.39839

ISSN

0021-8669;1533-3868

Language

en

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