A statistically designed experiment to characterize thrust augmentation for unsteady ejectors has been conducted at the NASA Glenn Research Center. The variable parameters included ejector diameter, length, and nose radius. The pulsed jet driving the ejectors was produced by a shrouded resonance (or Hartmann-Sprenger) tube. In contrast to steady ejectors, an optimum ejector diameter was found, which coincided with the diameter of the vortex ring created at the pulsed jet exit. Measurements of ejector exit velocity using a hot-wire permitted evaluation of the mass augmentation ratio, which was found to correlate to thrust augmentation following a formula derived for steady ejectors.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Unsteady Ejector Performance: An Experimental Investigation Using a Resonance Tube Driver


    Beteiligte:
    J. Wilson (Autor:in) / D. E. Paxson (Autor:in)

    Erscheinungsdatum :

    2002


    Format / Umfang :

    19 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch






    Unsteady Ejector Performance: An Experimental Investigation Using a Pulsejet Driver

    Paxson, Daniel / Wilson, Jack / Dougherty, Kevin | AIAA | 2002


    Unsteady Ejector Performance: An Experimental Investigation Using a Pulsejet Driver

    Paxson, D. E. / Wilson, J. / Dougherty, K. T. et al. | British Library Conference Proceedings | 2002