A low pressure oxygen/hydrogen turbine drive combustor hot-fire test series was conducted on the Turbine Drive Combustor Technology Program. The first objective was to gather data on an axisymmetric combustion system to support anchoring of a new combustion/fluid dynamics computer code under development on the same contract. The second objective was to gain insight into low mixture ratio combustion characteristics of coaxial injector elements.


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    Titel :

    Laser Schlieren and ultraviolet diagnostics of rocket combustion


    Beteiligte:
    Fisher, S. C. (Autor:in)


    Erscheinungsdatum :

    01.04.1985


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch






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