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Computational study of a battle damaged finite aspect ratio wing

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conference contribution
posted on 13.07.2012, 11:27 by Zhiyin Yang, Mujahid Samad-Suhaeb, Peter M. Render
Numerical studies have been carried out on a battle damaged NACA 641-412 half wing of aspect ratio 8.2 at a Reynolds number of 5.5 x 105. The simulated gunfire damage was represented by a single hole with a diameter of 0.2 wing chord. The hole was centred at half chord and at spanwise locations of 450mm and 650mm from wing root. Computational Fluid Dynamics (CFD) results have been compared with experimental data and a general overall good agreement has been obtained, in the flow features introduced by the damage. Furthermore, the flow field inside the damage hole and in the region downstream of the jet have been analysed in more detail using CFD.



  • Aeronautical, Automotive, Chemical and Materials Engineering


  • Aeronautical and Automotive Engineering


YANG, Z., SAMAD-SUHAEB, M. and RENDER, P.M., 2012. Computational study of a battle damaged finite aspect ratio wing. IN: Proceedings of the 30th AIAA Applied Aerodynamics Conference, New Orleans, USA, Paper AIAA 29022012, 9 pp.


© Peter Render. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.


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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:




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