Separation or breakaway of over-expanded gas from nozzle wall plays important role in estimation of thrust from rocket engine when run at altitudes considerably less than design; Rocket Dept of Bristol Siddeley Engines Ltd carried out tests on experimental combustion chambers having static pressure tappings in nozzle divergent section; it is shown that pressure at which gas separates is neither constant nor independent of nozzle length; mechanism separation; effect of separation on sea-level thrust of nozzle designed for high altitude is shown.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Jet separation in conical nozzles


    Weitere Titelangaben:

    Roy Aeronautical Soc -- J


    Beteiligte:
    Sunley, H.L.G. (Autor:in) / Ferriman, V.N. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1964


    Format / Umfang :

    11 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Shock predictions in conical nozzles

    KOSSEN, R. / MIGDAL, D. | AIAA | 1965


    SHOCK FORMATION IN CONICAL NOZZLES

    BADHAM, H. / DARWELL, H. M. | AIAA | 1963


    Shock-induced boundary layer separation in overexpanded conical exhaust nozzles

    Arens, M. / Spiegler, E. | Engineering Index Backfile | 1963


    Optimization of conical thrust nozzles.

    Hoffman, J. D. / Scofield, M. P. | NTRS | 1967


    Optimization of conical thrust nozzles.

    HOFFMAN, J. D. | AIAA | 1967