A mathematical model of hybrid combustion regression is derived which rationally encompasses the chemical kinetic and gasdynamic factors. Data from Smoot and Price (AIAA J. v3 p1408 1965) are used to confirm the resulting regression rate equation.


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    Titel :

    Hybrid Rocket Combustion Regression Rate Model


    Beteiligte:
    E. Miller (Autor:in)

    Erscheinungsdatum :

    1966


    Format / Umfang :

    2 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





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