Experimental combustion efficiencies of 11 different propellant combinations were determined in nominal 200 lb thrust rocket engine at three chamber lengths and compared with analytical results; data agreed with predicted results except for hydrazine, which may have decomposed in liquid phase, and ammonia-fluorine.


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    Title :

    Propellant vaporization as criterion for rocket-engine design -- Experimental performance, vaporization, and heat-transfer rates with various propellant combinations


    Additional title:

    NASA -- Memo


    Contributors:
    Clark, B.J. (author) / Hersch, M. (author) / Priem, R.J. (author)


    Publication date :

    1959


    Size :

    31 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English