Studies are carried out for hydrogen-fueled subsonic combustion ramjet engines; Bray's criterion is used to determine nozzle freezing point; nozzle performance is calculated by assuming equilibrium conditions up to freezing point and frozen flow from freezing point to nozzle exit; parameters include nozzle throat size, throat radius of curvature, nozzle shape, Mach number, altitude, equivalence ratio, and inlet kinetic energy efficiency; it is shown that recombination losses are not expected to be serious for Mach numbers up to 9 and free-stream dynamic pressures above 500 psf.


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    Title :

    Effects of exhaust nozzle recombination on hypersonic ramjet performance -- 2


    Additional title:

    AIAA-ASME -- Paper


    Contributors:

    Conference:

    AIAA-ASME Hypersonic Ramjet Conference ; 1963 Combustion


    Published in:

    Publication date :

    1963


    Size :

    12 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English