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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    Title :

    Numerical Simulation of Film-Cooled Ablative Rocket Nozzles


    Contributors:
    D. B. Landrum (author) / R. M. Beard (author)

    Publication date :

    1996


    Size :

    39 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English