A bipropellant rocket engine plume contamination test program was conducted in the AEDC Aerospace Chamber (10V). A 5-lbf-thrust rocket engine, burning MMH as the fuel and N2O4 as the oxidizer, was operated over a range of engine operating parameters in a cryogenically pumped vacuum chamber where the background pressure was maintained below 0.00001 torr. Using the electron beam fluorescence technique, species number densities and rotational temperture were measured in both the forward- and back-flow region of the plume exhaust. Additionally, Mie scattering measurements were performed for the forward-flow regions of the plume exhaust. (Author)


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    Titel :

    Bipropellant Engine Plume Contamination Program. Volume II. Chamber Measurements. Phase II


    Beteiligte:
    H. M. Powell (Autor:in) / L. L. Price (Autor:in) / R. E. Alt (Autor:in)

    Erscheinungsdatum :

    1979


    Format / Umfang :

    115 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch