A wind tunnel investigation has been conducted to evaluate the aerodynamic performance, stability, and control characteristics of a full-scale general aviation aircraft equipped with an advanced natural laminar flow wing. Force and moment data were measured over wide angle-of-attack and sideslip ranges and at Reynolds numbers from 1.4 million to 2.4 million based on the mean aerodynamic chord. Additional measurements determined the condition of the wing boundary layer and the wing stalling characteristics. The results showed that large regions of natural laminar flow existed on the wing which would significantly enhance the cruise performance of the configuration. Artificially tripping the boundary layer did not significantly affect the lift, stability, and control characteristics. Leading-edge modifications were effective in improving the stall resistance of the configuration, and resulted in only minor penalties in calculated cruise performance.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Wind-tunnel investigation of a general aviation airplane equipped with a high aspect-ratio, natural laminar-flow wing


    Beteiligte:

    Erscheinungsdatum :

    1987-04-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Wind-Tunnel Investigation of a General Aviation Airplane Equipped With a High Aspect-Ratio, Natural-Laminar-Flow Wing

    Murri, Daniel G. / Jordan, Frank L. / Davis, Patrick J. et al. | SAE Technical Papers | 1987




    Flexible High Aspect Ratio Wing Wind Tunnel Tests

    Coetzee, Etienne / Lowenberg, Mark H. / Neild, Simon A. | AIAA | 2023


    Flexible High Aspect Ratio Wing Wind Tunnel Tests

    Coetzee, Etienne / Lowenberg, Mark H. / Neild, Simon A. | TIBKAT | 2023