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Experimental investigation of vortex dynamics on a 65° delta wing in sideslip

Published online by Cambridge University Press:  04 July 2016

G. Guglieri  and
F.B. Quagliotti
G. Guglieri
Affiliation:
Politecnico di Torino Dipartimento di Ingegneria Aeronautica e Spaziale, Torino, Italy
F.B. Quagliotti
Affiliation:
Politecnico di Torino Dipartimento di Ingegneria Aeronautica e Spaziale, Torino, Italy
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Abstract

The flow structure on the upper side of a delta wing is extremely complex. At moderate angle of attack the flowfield is dominated by organised vortical flow structures emanating from the leading edge. The pressure distribution created on the wing surface by these leading edge vortices causes an increment of lift which may be a relevant percentage of the total wing lift, depending on sweep angle.

Delta wing performance is conditioned, however, by a phenomenon known as vortex breakdown or vortex bursting which appears at high angle of attack. This leads to a drastic change in the flowfield which influences the trend of the aerodynamic coefficients.

With the aim of giving a contribution to the understanding of the phenomenon of vortex breakdown, a 65° delta wing has been extensively tested in the low speed windtunnel of Politecnico di Torino (TPI) both in static and dynamic conditions, under forced oscillatory motions.

Many experiments have been carried out in an effort to understand the factors which can affect the breakdown by varying angle of attack, sideslip angle and Reynolds number.

Flow visualizations have been performed using helium bubble tracers. This technique showed a very good capability for visualizing vortical flows and breakdown, both in static and dynamic conditions.

For the static case, pressure distributions are presented, correlated to force measurements and flow visualizations, at different angles of attack and sideslip for different flow conditions.

For the dynamic case force measurements are shown, compared with flow visualizations, for different angles of attack and for different oscillation frequencies.

Type
Research Article
Information
The Aeronautical Journal , Volume 101 , Issue 1003 , March 1997 , pp. 111 - 120
Copyright
Copyright © Royal Aeronautical Society 1997 

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