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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    Title :

    Heat transfer investigation of ejector systems with 90° turns


    Additional title:

    AIAA -- Tech Paper


    Contributors:
    Patmor, G.O. (author) / Nelson, R.E. (author) / Mandell, B. (author) / McFarland, B.L. (author)

    Conference:

    AIAA -- Space Simulation Testing Conference ; 1964 Heat problems



    Publication date :

    1964


    Size :

    6 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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



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