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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    Title :

    Ablative stagnation point heat transfer


    Additional title:

    CASI Trans


    Contributors:


    Publication date :

    1969


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English