Loughborough University
Browse

Investigation of the flowfield induced by simulated battle damage

Download (2.42 MB)
journal contribution
posted on 2017-03-24, 15:57 authored by Mathew Almond, Peter Render, Duncan WalkerDuncan 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

Volume

121

Issue

1243

Pages

1296 - 1318

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

2017-02-27

Publication date

2017-08-25

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

Usage metrics

    Loughborough Publications

    Exports

    RefWorks
    BibTeX
    Ref. manager
    Endnote
    DataCite
    NLM
    DC