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)


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    Title :

    Subsonic vortex-flow design study for slender wings


    Additional title:

    Eine Unterschall-Wirbelstroemungs-Entwurfsstudie fuer schlanke Tragflaechen


    Contributors:
    Lamar, J.E. (author)

    Published in:

    Publication date :

    1978


    Size :

    9 Seiten, 18 Bilder, 11 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English