Proposal for steadying flow from rocket nozzle on Space Shuttle main engine could be applied to other large-area-ratio contoured nozzles. Oscillations and pulsations in boundary-layer flow would be reduced by flaring nozzle exit. Transient side loads on nozzle would be suppressed. Large pressure gradients and eddies that can lead to fluctuations are suppressed. Exact radius of curvature of corner would depend on shear-layer thickness.


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    Titel :

    Nozzle Modification Suppresses Flow Transients


    Beteiligte:
    Rao, G. V. R. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1982-09-01



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



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    Experimental Investigation of Mixing Enhancement Through Nozzle Exit Modification in Subsonic Flow

    Vijayaraj, T. / Thanigaiarasu, S. / Jabez Richards, S. B. et al. | Springer Verlag | 2020


    Nozzle Flow Summary

    Emanuel, George | AIAA | 1986