Principal drawback of graphite for use as rocket nozzle throat insert is its erosivity; erosion of inserts is explained on basis of chemical mechanism if account is taken of chemical composition of exhaust stream, geometrical and temperature history of insert, ballistic effects of erosion, rates of diffusion of molecular species through boundary layer, and chemical kinetics of surface reactions; results of erosion calculation.


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    Title :

    Semiquantitative prediction of erosion of graphite nozzle inserts


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 2 , n 8


    Publication date :

    1964


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    A semiquantitative prediction of the erosion of graphite nozzle inserts

    DELANEY, L. J. / EAGLETON, L. C. / JONES, W. H. | AIAA | 1964


    A semi-quantitative prediction of the erosion of graphite nozzle inserts

    DELANEY, L. / EAGLETON, L. / JONES, W. | AIAA | 1964


    Erosion of nozzle throat inserts and silica-phenolic ablative liner morphology

    DE, GANGADHAR / NARENDRANATH, M. / SARKAR, B. K. | AIAA | 1990


    Chemical Erosion of Refractory Metal Nozzle Inserts in Solid-Propellant Rocket Motors

    Thakre, P. / Yang, V. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2008