Subsonic wind tunnel tests were conducted to determine performance improvements possible from the use of leading edge vortex flaps (LEVF) on delta wings. Various flap sizes and deflection angles were examined and lift-to-drag ratio improvements of up to 40% were found at moderate angles of attack on 60 deg and 75 deg swept wings. The LEVF is concluded to be effective in moving the wing's leading edge vortex onto the flaps, tilting the vortex-induced force vector forward to produce a thrust or reduce the wing's drag while maintaining attached flow and lift on the wing's upper surface.
Performance improvement of delta wings at subsonic speeds due to vortex flaps
Aircraft Systems Meeting ; 1980 ; Anaheim, CA
1980-08-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Aerodynamics of delta wings with flaps at hypersonic speeds
Online Contents | 2002
|Experimental Investigation of Thick Delta Wings with Vortex Flaps
British Library Conference Proceedings | 1994
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