Based on premise that supersonic burning is possible, performance of ramjet cycles is calculated over range of flight Mach numbers from 4 to 7; effects of parameters such an inlet design, combustor area, divergence, wall friction, and nozzle performance; estimates of engine weight and cooling loads included.


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    Title :

    Analysis of ramjet engines using supersonic combustion


    Additional title:

    NACA -- Tech Note


    Contributors:
    Weber, R.J. (author) / Mackay, J.S. (author)

    Published in:

    Publication date :

    1958


    Size :

    49 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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