Requirement to design light weight heat shields for sounding rockets has focused attention on solution of general equations of fluid dynamics coupled with mathematical ablation model for subliming ablators; to test accuracy, of theory and model, two monitored inflight rocket experiments were performed using Black Brant rockets as experimental platforms; comparison of experimental data and results obtained from theory, programmed for IBM 360 computer shows good agreement over wide range of flight conditions for continuum supersonic and hypersonic regimes. (29773)


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    Titel :

    Ablative stagnation point heat transfer


    Weitere Titelangaben:

    CASI Trans


    Beteiligte:
    Richman, J.W. (Autor:in)


    Erscheinungsdatum :

    1969


    Format / Umfang :

    6 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :