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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    Titel :

    Pulse Detonation Rocket Engine Research at NASA Marshall


    Beteiligte:

    Kongress:

    16th ONR Propulsion Meeting ; 2003 ; Los Angeles, CA, United States


    Erscheinungsdatum :

    2003-05-09


    Medientyp :

    Preprint


    Format :

    Keine Angabe


    Sprache :

    Englisch