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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Nozzle Modification Suppresses Flow Transients


    Contributors:

    Published in:

    Publication date :

    1982-09-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :



    Transients in Homogeneous Granular Pipe Flow

    Schaefer, J. / Wolf, D. E. / German Supercomputing Center HLRZ | British Library Conference Proceedings | 1996


    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


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

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


    Jet Noise Modification by the Whistler Nozzle.

    M.A.Z. Hasan / A.K.M.F. Hussain | AIAA | 1984