D.G. Mabey, C.R. Pyne

The main features of fin buffeting on a slender wing at high angles of incidence were established by tests on a complete model of the Concorde aircraft in the RAE 13ft x 9ft LOW Speed Wind Tunnel. The measurements comprise overall steady forces, buffeting on the fin and the wing and some surface flow visualisation. The fin buffeting is more severe than the wing buffeting. Thus when a tightly rolled vortex is present on the wing upper surface the wing buffeting is "light" whereas the fin buffeting is "heavy". After vortex breakdown the wing buffeting is "heavy" whereas the fin buffeting is "very heavy". It was shown that vortex breakdown can be delayed by axial injection of air along the vortex core upstream of the burst point. Besides improving the static force characteristics, this reduces the fin and wing buffeting.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.552-561; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991