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A computational study of laminar-flow secondary separation on a slender delta wing

Published online by Cambridge University Press:  12 September 2018

I. P. Jones Open the ORCID record for I. P. Jones [Opens in a new window]  and
N. Riley
I. P. Jones*
Affiliation:
Formerly ANSYS UK, WantageOxfordshire, UK
N. Riley
Affiliation:
School of Mathematics, University of East Anglia Norwich Research Park Norwich, UK
*
ian.jones999@gmail.com
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Abstract

The laminar flow over a slender delta wing at incidence has been extensively studied both experimentally and theoretically using vortex sheet methods. These vortex sheet methods have generally been successful apart from the prediction of the secondary boundary-layer separation induced by the primary vortex. This paper revisits the problem using computational fluid dynamics (CFD) and focusses on the effects of the secondary flow separation. The modelling approach is briefly summarised, and the results are compared with flow measurements and results from vortex sheet methods. The computations show very good agreement with measurements for the surface pressures and total head contours. The results help to understand the complex structure of the leading edge vortex flow, and the associated secondary separation of the boundary layer. They indicate that inviscid mechanisms dominate the larger scale features, and highlight a possible mechanism for the development of an instability in the leading edge vortex sheet.

Keywords

Delta wingsleading edge vorticessecondary flow separationvortex sheetscomputational fluid dynamicslaminar flowvalidation
Type
Research Article
Information
The Aeronautical Journal , Volume 122 , Issue 1256 , October 2018 , pp. 1654 - 1672
Copyright
© Royal Aeronautical Society 2018 

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