Computational study of a battle damaged finite aspect ratio wing
conference contributionposted on 13.07.2012 by Zhiyin Yang, Mujahid Samad-Suhaeb, Peter M. Render
Any type of content contributed to an academic conference, such as papers, presentations, lectures or proceedings.
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