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The influence of simulated missile warhead fragment damage on the aerodynamic characteristics of two-dimensional wings

Published online by Cambridge University Press:  27 January 2016

A. J. Irwin  and
P. M. Render
A. J. Irwin
Affiliation:
BAE Systems Warton, UK
P. M. Render*
Affiliation:
Department of Aeronautical and Automotive Engineering, Loughborough University, Loughborough, UK
*
P.M.Render@lboro.ac.uk
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Abstract

The paper describes a method of representing damage on a wing due to multiple warhead fragments, and investigates two of the key variables: fragment impact density and hole diameter. The aerodynamic effects of the damage were quantified by wind-tunnel tests on a two-dimensional wing at a Reynolds number of 5 × 105. The wing was of hollow construction with leading and trailing-edge spars. In all of the cases tested, simulated fragment damage resulted in significant lift losses, drag increases and pitching moment changes. Increasing fragment density or hole size resulted in greater effects. To a first order approximation, both lift and drag increments at a given incidence were related to the percentage wing area removed. Surface flow visualisation showed that low fragment densities and small damage sizes resulted in a complex flow structure on the surface of the wing. This was made up of boundary-layer growth between the damage holes, attached wakes from the forward damage holes and separated surface flow over the rear of the wing. For these cases, individual hole patterns showed similar flow mechanisms to those seen for larger scale gunfire damage cases. Increased fragment density and hole size resulted in upper surface flow separation at the first row of holes. Behind this separation, the flow was attached and consisted of the combined wakes from the forward damage holes. Investigations into the influence of internal model structure indicated that trends in coefficient changes were similar for both hollow and solid wings. However, the magnitudes of the effects were found to be smaller for hollow wings than for solid wings.

Type
Research Article
Information
The Aeronautical Journal , Volume 117 , Issue 1194 , August 2013 , pp. 823 - 837
Copyright
Copyright © Royal Aeronautical Society 2013 

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