The 'Vortex Flap' is a novel concept aimed at reducing the lift-dependent drag due to leading-edge flow separation on highly swept, slender wings at high angles of attack. The suction effect of coiled vortices generated via controlled separation over leading-edge flap surfaces is utilized to produce an aerodynamic thrust component. This principle was verified through wind-tunnel experiments on 74-deg and 60-deg delta wings and a supersonic-cruise slender wing aircraft configuration. Adaptation of the vortex-flap for augmentation of roll-control on the 74-deg delta at high angles of attack also was demonstrated. Selected results are presented in this paper to indicate the potential of the vortex flap concept to enhance the low-speed performance, stability and control of slender wing aircraft.
Leading-edge 'Vortex Flaps' for enhanced subsonic aerodynamics of slender wings
International Council of the Aeronautical Sciences, Congress ; 1980 ; Munich, Germany
01.01.1980
Sonstige
Keine Angabe
Englisch
Aerodynamics of maneuvering slender wings with leading-edge separation
Tema Archiv | 1993
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