Abstract
Subsonic wind tunnel investigations were conducted on delta wings with tabbed vortex flaps. The tab comprises an up-deflected leading-edge portion of the flap intended to augment the vortex-induced thrust on the down-deflected flap. Balance and pressure measurements on a 74-deg delta model compared plane and tabbed vortex flaps of equal total area; tab modifications intended to improve the L/D over plane flaps were evaluated. In a parallel investigation, detailed spanwise pressures were measured on a 65-deg delta wing model from which sectional lift and drag contributions of the individual wing, flap, and tab surfaces were obtained by integration. Theoretical solutions using the free vortex sheet code with several flap/tab deflections on the 65-deg delta were compared with experimental pressures and vortex core positions. The results of this exploratory study showed that while the tab can augment the flap vortex thrust considerably, an excessive tab drag component may cancel this benefit. Preliminary guidelines toward more efficient tab configurations have been suggested.
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