A theoretical study describing the effects of spanwise camber on the lift dependent drag of slender delta wings having leading-edge-vortex-flow is presented. The earlier work by Barsby, using conical flow, indicated that drag levels similar to those in attached flow could be obtained. This is reexamined and then extendel to the more practical case of nonconical flow by application of the vortex-lattice method coupled with the suction-analogy and the recently developed Boeing free-vortex-sheet method. Lastly, a design code is introduced which employs the suction analogy in an attempt to define 'optimum' camber surfaces for mimimum lift dependent drag for vortex flow conditions.(Buehn)
Subsonic vortex-flow design study for slender wings
Eine Unterschall-Wirbelstroemungs-Entwurfsstudie fuer schlanke Tragflaechen
AIAA-Papers ; 1-9
1978
9 Seiten, 18 Bilder, 11 Quellen
Conference paper
English
Subsonic Vortex-Flow Design Study for Slender Wings
AIAA | 1978
|Subsonic vortex-flow design study for slender wings
AIAA | 1978
|Subsonic wing rock of slender delta wings
AIAA | 1985
|Sulsonic vortex-flow desig study for slender wings
Tema Archive | 1978
|