The linear stability of a fully three-dimensional boundary layer formed over a general aviation fuselage was investigated. The location of the onset of transition was estimated using the N-factor method. The results were compared with existing experimental data and indicate N-factors of approximately 8.5 on the side of the fuselage and 3.0 near the top. Considerable crossflow existed along the side of the body, which significantly affected the unstable modes present in the boundary layer. Fair agreement was found between the predicted frequency range of linear instability modes and available experimental data concerning the spectral content of the boundary layer.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Stability theory and transition prediction applied to a general aviation fuselage


    Beteiligte:
    Spall, R. E. (Autor:in) / Wie, Y.-S. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.04.1993



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :




    Le Fuselage En Aviation

    Boccaccio, P. | Engineering Index Backfile | 1916


    Low Cost Manufacturing Method for a General Aviation Aircraft Fuselage

    Simpson, C. / Ta ala, B. / Anderson, A. et al. | British Library Conference Proceedings | 2003


    Crashworthy Composite Fuselage Section Concept for Next Generation General Aviation

    Maia, Leandro Guimarães / de Oliveira, Paulo Henriques Iscold Andrade | SAE Technical Papers | 2005