Method is presented for using injector pattern design as basis for estimating gas composition and flow patterns in combustion zone of rocket engine; principles of gas-dynamics are applied to determine magnitude and direction of lateral flow in chamber as function of axial station; stream tube theory allows evaluation of chemical composition at any local area; from these data critical zones at chamber wall may be located and requirements for satisfactory protection determined; two examples and results of analysis are given.


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    Titel :

    Environmental effects upon rocket injector/chamber compatibility


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Conn, T.E. (Autor:in) / Hester, J.N. (Autor:in) / Valentine, R.S. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1967


    Format / Umfang :

    5 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Environmental effects upon rocket injector/ chamber compatibility.

    CONN, T. E. / HESTER, J. N. / VALENTINE, R. S. | AIAA | 1967



    Rocket Injector Head

    C. W. Green | NTIS | 1966


    Rocket injector head

    Green, C. W., Jr. | NTRS | 1968


    Shear coaxial injector spray combustion experiments in a single element rocket chamber

    Maskery, A / Puissant, C / Glogowski, M et al. | AIAA | 1995