Loughborough University
Leicestershire, UK
LE11 3TU
+44 (0)1509 263171
Loughborough University

Loughborough University Institutional Repository

Please use this identifier to cite or link to this item: https://dspace.lboro.ac.uk/2134/12607

Title: A technique to predict the aerodynamic losses of battle damaged wings
Authors: Pickhaver, T.W.
Render, Peter M.
Keywords: Aerodynamics
Wind tunnel testing
Battle damage
Finite aspect ratio
Two dimensional testing
Prediction techniques
Issue Date: 2012
Publisher: ICAS
Citation: PICKHAVER, T.W. and RENDER, P.M., 2012. A technique to predict the aerodynamic losses of battle damaged wings. 28th International Congress of Aeronautical Sciences, Brisbane, Australia, 23 September 2012, 15 pp.
Abstract: Development of a technique to predict the effects of simulated battle damage on the aerodynamics of a three dimensional wing is described. A methodology for converting two dimensional lift, drag and pitching moment data to three dimensional values is developed. To test this methodology, wind tunnel testing was carried out on a three dimensional half model of the NASA LS(1)-0417MOD aerofoil, with simulated battle damage. The effective aspect ratio of the model was 6. A circular hole with a diameter of 20% of wing chord was used to simulate gunfiretype battle damage. To model different attack directions the axis of the hole was inclined along the chord and span. Three spanwise locations for the damage were tested. Testing was undertaken at a Reynolds Number of 1,000,000. Compared to an undamaged wing, the addition of damage caused an increase in drag, a decrease in lift and a more negative pitching moment. The effects increased with incidence and changed with hole orientation. These effects were reduced as the damage was moved towards the wing tip. Results from the predictive technique were compared with those from half model testing. The predicted lift loss was seen to be in close agreement with wind tunnel results, but the drag increase was under predicted. The biggest errors in the prediction occurred for the pitching moment, although the relatively low aspect ratio is believed to have an adverse effect on the comparison.
Description: This is a conference paper [ICAS 2012-3.2.2]. It was presented at the 28th Congress of the International Council of the Aeronautical Sciences, 23 - 28 September 2012, Brisbane, Australia.
Version: Accepted for publication
URI: https://dspace.lboro.ac.uk/2134/12607
Publisher Link: http://www.icas.org/ICAS_ARCHIVE/ICAS2012/ABSTRACTS/273.HTM
ISBN: 978-0-9565333-1-9
Appears in Collections:Conference Papers and Presentations (Aeronautical and Automotive Engineering)

Files associated with this item:

File Description SizeFormat
ICAS 2012 Final.pdfAccepted version641.46 kBAdobe PDFView/Open

 

SFX Query

Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.