Results from test program which evaluated heat transfer characteristics of ejector systems that turned rocket exhaust gases through 90° show differences in thermal behavior that can be obtained during turning of gases; maximum heating rate was reduced by factor of seven when ejector had long radius, as compared to short radius 90° turn and by factor of five by permitting gases to shock down to subsonic flow prior to entering short radius bend; method of converting scale-model heat-transfer coefficient data to any other scale size, working fluid, nozzle chamber temperature or chamber pressure and empirical correlation of maximum heating rates is presented.


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    Titel :

    Heat transfer investigation of ejector systems with 90° turns


    Weitere Titelangaben:

    AIAA -- Tech Paper


    Beteiligte:
    Patmor, G.O. (Autor:in) / Nelson, R.E. (Autor:in) / Mandell, B. (Autor:in) / McFarland, B.L. (Autor:in)

    Kongress:

    AIAA -- Space Simulation Testing Conference ; 1964 Heat problems



    Erscheinungsdatum :

    1964


    Format / Umfang :

    6 pages


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    A HEAT TRANSFER INVESTIGATION OF EJECTOR SYSTEMS WITH 90 DEGREE TURNS

    MANDELL, B. / NELSON, R. / PATMOR, G. et al. | AIAA | 1964


    A Heat Transfer Investigation of Ejector Systems with 90 Deg Turns. Nerva Program

    B. Mandell / B. L. Mc Farland / R. E. Nelson et al. | NTIS | 1964



    Calculation of Aerodynamic Performance and Heat Transfer of an Ejector Nozzle

    Qian, Y. / He, H. / Beijing University of Aeronautics and Astronautics | British Library Conference Proceedings | 1994


    HEAT EJECTOR OF AN ENGINE

    SHIN MYUNG HO | Europäisches Patentamt | 2019

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