Pulse detonation rocket engines (PDREs) offer potential performance improvements over conventional designs, but represent a challenging modeling task. A quasi 1-D, finite-rate chemistry CFD model for a PDRE is described and implemented. A parametric study of the effect of blowdown pressure ratio on the performance of an optimized, fixed PDRE nozzle configuration is reported. The results are compared to a steady-state rocket system using similar modeling assumptions.


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    Title :

    Pulse Detonation Rocket Engine Research at NASA Marshall


    Contributors:

    Publication date :

    2003


    Size :

    6 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English