Correlations for transition from laminar to turbulent flow on 45° and 60° swept cylinders based on data obtained in the NASA Langley Mach 3.5 Pilot Quiet Tunnel are presented. Variations of free-stream noise from high levels comparable to those in conventional wind tunnels to more than an order of magnitude lower had no effect on transition. However, when boundary-layer trips were attached to the leading edges, transition occurred at lower Reynolds numbers depending on both the trip height and the wind tunnel noise level.Compressible linear stability calculations have been performed for the boundary layer on an infinite swept cylinder. The boundary layer on the attachment line has a generalized inflection point similar to that present in a flat-plate boundary layer. The results show that Tollmien-Schlichting waves are amplified in the attachment line boundary layer and that oblique waves have the highest growth rates. Wall cooling tends to be stabilizing. Calculations for the wavelengths of stationary cross-flow vortices that occur downstream of the attachment line are compared with experimental values.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Boundary-Layer Instability Mechanisms on a Swept-Leading Edge at Mach 3.5


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:
    Beckwith, I. E. (Autor:in) / Malik, M. R. (Autor:in) / Creel, T. R. (Autor:in)

    Kongress:

    Aerospace Technology Conference and Exposition ; 1987



    Erscheinungsdatum :

    01.10.1987




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    Boundary-layer instability mechanisms on a swept-leading edge at Mach 3.5

    Creel, T.R. jun. / Malik, M.R. / Beckwith, I.E. | Tema Archiv | 1987


    Leading edge transition on a 76 degree swept cylinder at Mach 1.6

    Coleman, Colin / Laub, James / Poll, D. et al. | AIAA | 1996


    Leading Edge Transition on a 76 Degree Swept Cylinder at Mach 1.6

    Coleman, C. P. / Poll, D. I. A. / Laub, J. A. et al. | British Library Conference Proceedings | 1996


    Transition on swept leading edges at Mach 3.5

    Creel, T. R., Jr. / Beckwith, I. E. / Chen, F. J. | NTRS | 1987


    Transition on swept leading edges at Mach 3.5

    CREEL, T. R. / BECKWITH, I. E. / CHEN, F. J. | AIAA | 1987