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Vortex interaction and breakdown over double-delta wings

Published online by Cambridge University Press:  03 February 2016

S. L. Gai ,
M. Roberts ,
A. Barker ,
C. Kleczaj  and
A. J. Riley
S. L. Gai
Affiliation:
School of Aerospace & Mechanical Engineering, University of New South Wales, Canberra, Australia
M. Roberts
Affiliation:
School of Aerospace & Mechanical Engineering, University of New South Wales, Canberra, Australia
A. Barker
Affiliation:
School of Aerospace & Mechanical Engineering, University of New South Wales, Canberra, Australia
C. Kleczaj
Affiliation:
School of Aerospace & Mechanical Engineering, University of New South Wales, Canberra, Australia
A. J. Riley
Affiliation:
School of Aerospace & Mechanical Engineering, University of New South Wales, Canberra, Australia
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Abstract

Modern high-speed aircraft, especially military, are very often equipped with single or compound delta wings. When such aircraft operate at high angles-of-attack, the major portion of the lift is sustained by streamwise vortices generated at the leading edges of the wing. This vortex-dominated flow field can breakdown, leading not only to loss of lift but also to adverse interactions with other airframe components such as the fin or horizontal tail. The wind tunnel and water studies described herein attempt to clarify the fluid mechanics of interaction between the strake and wing vortices of a generic 76°/40° double-delta wing leading to vortex breakdown. Some studies of passive control using fences at the apex and kink region are also described. Various diagnostic methods-laser sheet flow visualisation, fluorescent dyes, and pressure sensitive paints have been used.

Type
Research Article
Information
The Aeronautical Journal , Volume 108 , Issue 1079 , January 2004 , pp. 27 - 34
Copyright
Copyright © Royal Aeronautical Society 2004 

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