A previously developed technique for selecting a design space for efficient supersonic wings is reviewed; this design-space concept is expanded to include thickness and camber effects and is evaluated for cambered wings at high-lift conditions. The original design-space formulation was based on experimental upper-surface and lower-surface normal-force characteristics for flat, uncambered delta wings; it is shown that these general characteristics hold for various thickness distributions and for various amounts of leading-edge camber. The original design-space formulation was also based on the assumption that the combination of Mach number and leading-edge sweep which would produce an equal division of flat-wing lift between the upper and lower surface would also be the proper combination to give the best cambered-wing performance. Using drag-due-to-lift factor as a measure of performance, for high-lift conditions cambered-wing performance is shown to significantly increase as conditions approach the design space; this correlation is demonstrated for both subcritical and supercritical flows.


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    Title :

    Aerodynamic design considerations for efficient high-lift supersonic wings


    Contributors:
    Miller, D. S. (author) / Wood, R. M. (author)

    Publication date :

    1985-10-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :



    Aerodynamic design of supersonic wings with high aerodynamic efficiency

    Radespiel, R. / Stilla, J. / Eggers, T. et al. | British Library Conference Proceedings | 1995