This report describes the experimental data and the procedures used in acquiring and reducing the thermal loads data during tests of a hydrocarbon- fueled scramjet combustor at United Technologies Research Center (UTRC). This research effort is part of the UTRC effort to develop dual-mode scramjet combustor technology to support the development of Mach S missile technology. The objective of the thermal loads testing was to map the thermal and mechanical loads, including heat transfer, dynamic and static pressures, and skin friction in a scramjet combustor during direct-connect scramjet tests. The tests were conducted at the UTRC Ramject/Scramjet direct-connect combustor test facility in East Hartford, CT.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Thermal Performance of a Scramjet Combustor Operating at Mach 5.6 Flight Conditions


    Beteiligte:
    S. D. Stouffer (Autor:in) / R. D. Neumann (Autor:in) / D. S. Emmer (Autor:in)

    Erscheinungsdatum :

    1997


    Format / Umfang :

    145 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Circular Scramjet Combustor Transition Lengths at Mach 8 and 12.8 Flight Conditions

    van Staden, Paul A. / Lorrain, Philippe / Brown, Melrose L. et al. | AIAA | 2020


    Scramjet Combustor Characteristics at Hypervelocity Condition over Mach 10 Flight

    Takahashi, M. / Komuro, T. / Sato, K. et al. | British Library Conference Proceedings | 2009


    Improvement of Scramjet Combustor Performance at Hypervelocity Condition over Mach 10 Flight

    Takahashi, Masahiro / Komuro, Tomoyuki / Sato, Kazuo et al. | AIAA | 2008


    Improvement of Scramjet Combustor Performance at Hypervelocity Condition over Mach 10 Flight

    Takahashi, M. / Komuro, T. / Sato, K. et al. | British Library Conference Proceedings | 2008