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This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License
Article
Author(s)
William Ruffles and Sam M. Dakka
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DOI:10.17265/1548-7709/2016.06.004
Affiliation(s)
Department of Engineering and Math, Sheffield Hallam University, Howard Street, Sheffield S1 1WB, United Kingdom
ABSTRACT
Computational fluid dynamic tests are performed on delta wing models at
different heights and speeds in order to achieve lift and drag coefficient
values. Primarily, testing was done at supersonic
speeds to reveal the advantages of these wing configurations at supersonic
flight regimes at a cruise speed and altitude. The low speed characteristics
are also examined, important for
take-off and landing regimes where the distinctive
vortices become prominent. Throughout the two flight conditions tested, a
simple delta wing model (with a straight swept wing) is compared to a delta
wing model that exhibited an LERX (leading edge root
extension). Provided literature describes how the performance of delta wings
can be improved through this inclusion. Results obtained from the tests show
that the model with the LERX has a small, but significant, performance
improvement over the simple delta model, in respect to the maximum achievable
lift coefficient and maximum stall angle. Lift to drag ratio is not improved
however, due to the large vortices creating pressure drag. Generally, the delta
wing models produce relatively small amounts of drag, and slightly less lower
lift, when at low angles of attack. This is primarily due to the geometry of
the models that have thin leading edges and also low thickness to chord ratios.
KEYWORDS
LERX, vortex breakdown, vortex burst, buffeting, maximum lift coefficient, maximum stall angle.
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