Almond et al..pdf (2.42 MB)
0/0

Investigation of the flowfield induced by simulated battle damage

Download (2.42 MB)
journal contribution
posted on 24.03.2017 by Mathew Almond, Peter Render, Duncan Walker, A. Howlett
Particle Image Velocimetry (PIV) has been used to study the complex flowfield created by simulated battle damage to a two-dimensional wing. Computational Fluid Dynamics (CFD) predictions have also been used for validation of internal cavity flow. Two damage cases were selected for the study; both cases were simulated using a single hole with diameters equal to 20% and 40% of the chord, located at the wing half-chord. Wind tunnel tests were conducted at a Reynolds number of 500,000 over a range of incidences from 0 to 10◦ with two-component PIV measurements made on three chordwise and three spanwise planes. The PIV data were analysed and compared to CFD data of the same damage cases. The PIV data have shown lower velocity ratios and lower vorticity in the jet compared to past Jet in Cross-Flow experiments and CFD was used to describe the flow features inside the cavity of the wing. It was seen that the wing cavity has large effects on the external flow features, particularly for the 20% damage case. Finally, the flow field data have been related to force balance data. At higher incidence angles, the larger force coefficient increments in both lift and drag can be attributed to the larger wakes and higher jet strengths.

History

School

  • Aeronautical, Automotive, Chemical and Materials Engineering

Department

  • Aeronautical and Automotive Engineering

Published in

The Aeronautical Journal

Citation

ALMOND, M.T. ... et al, 2017. Investigation of the flowfield induced by simulated battle damage. The Aeronautical Journal, 121(1243), pp.1296-1318.

Publisher

Cambridge University Press © Royal Aeronautical Society

Version

AM (Accepted Manuscript)

Publisher statement

This work is made available according to the conditions of the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International (CC BY-NC-ND 4.0) licence. Full details of this licence are available at: https://creativecommons.org/licenses/by-nc-nd/4.0/

Acceptance date

28/02/2017

Publication date

2017

Notes

This paper was accepted for publication in the journal The Aeronautical Journal and the definitive published version is available at https://doi.org/10.1017/aer.2017.58

ISSN

0001-9240

eISSN

2059-6464

Language

en

Exports

Logo branding

Keyword(s)

Exports