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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    Title :

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


    Contributors:
    H. M. Powell (author) / L. L. Price (author) / R. E. Alt (author)

    Publication date :

    1979


    Size :

    115 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English