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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    Title :

    Laser Schlieren and ultraviolet diagnostics of rocket combustion


    Contributors:


    Publication date :

    1985-04-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English






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