The objective of this research effort was to evaluate the impact of incorporating an additional cooling port downstream between the injector and nozzle throat in the NASA Fast Track chamber. A numerical model of the chamber was developed for the analysis. The analysis did not model ablation but instead correlated the initial ablation rate with the initial nozzle wall temperature distribution. The results of this study provide guidance in the development of a potentially lighter, second generation ablative rocket nozzle which maintains desired performance levels.


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    Titel :

    Numerical Simulation of Film-Cooled Ablative Rocket Nozzles


    Beteiligte:
    D. B. Landrum (Autor:in) / R. M. Beard (Autor:in)

    Erscheinungsdatum :

    1996


    Format / Umfang :

    39 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Numerical simulation of film-cooled ablative rocket nozzles

    Landrum, D. B. / Beard, R. M. | NTRS | 1996





    Kinetic performance of barrier-cooled rocket nozzles.

    FREY, H. M. / KLIEGEL, J. R. | AIAA | 1968