A composite wing extension was designed for a typical general aviation aircraft to improve lift curve slope, dihedral effect, and lift to drag ratio. Advanced composite materials were used in the design to evaluate their use as primary structural components in general aviation aircraft. Extensive wind tunnel tests were used to evaluate six extension shapes. The extension shape chosen as the best choice was 28 inches long with a total area of 17 square feet. Subsequent flight tests showed the wing extension's predicted aerodynamic improvements to be correct. The structural design of the wing extension consisted of a hybrid laminate carbon core with outer layers of Kevlar - layed up over a foam interior which acted as an internal support. The laminate skin of the wing extension was designed from strength requirements, and the foam core was included to prevent buckling. A joint lap was recommended to attach the wing extension to the main wing structure.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Design of a Composite Wing Extension for a General Aviation Aircraft


    Contributors:
    P. S. Adney (author) / W. J. Horn (author)

    Publication date :

    1984


    Size :

    49 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Modern Wing Technology for General Aviation Aircraft

    M. Lotz / B. Huinink / W. Haberland et al. | NTIS | 1977



    Low Cost Composite Manufacturing Method for a General Aviation Aircraft Wing

    Teufel, P. / Maxwell, M. / Gardiner, R. et al. | British Library Conference Proceedings | 2003


    Preliminary Wing Study of General Aviation Aircraft with Stitched Composite Panels

    Papapetrou, Vasileios S. / Tamijani, Ali Y. / Kim, Daewon | AIAA | 2017