The effect of roughness on the heat transfer distributions and the transition criteria for the windward pitch plane of the shuttle orbiter at an angle of attack of 30 deg was studied using data obtained in hypersonic wind tunnels. The heat transfer distributions and the transition locations for the roughened models were compared with the corresponding data for smooth models. The data were correlated using theoretical solutions for a nonsimilar, laminar boundary layer subject to two different flow field models for the orbiter.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Hypersonic heat-transfer and transition correlations for a roughened shuttle orbiter


    Beteiligte:
    Bertin, J. J. (Autor:in) / Stalmach, D. D. (Autor:in) / Idar, E. S., III (Autor:in) / Conley, D. B. (Autor:in) / Goodrich, W. D. (Autor:in)


    Erscheinungsdatum :

    01.01.1976


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch






    Experimental and computational analysis of Shuttle Orbiter hypersonic trim anomaly

    Brauckmann, Gregory J. / Paulson, John W. / Weilmuenster, K. J. | AIAA | 1995


    Experimental and Computational Analysis of Shuttle Orbiter Hypersonic Trim Anomaly

    Brauckmann, Gregory J. / Paulson, John W., Jr. / Weilmuenster, K. James | NTRS | 1995