Optimization of a Prop-Fan propulsion system for a Mach 0.8, 120 passenger commercial transport has shown the need for relatively high levels of overall pressure ratio, combustor exit temperature, propeller tip speed and propeller disk loading to achieve lowest fuel burn and direct operating costs. Comparison of this optimized Prop-Fan propulsion system with an equivalent technology turbofan showed it to have significant mission fuel burn and direct operating cost advantages.


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    Title :

    Some Aspects of Prop-Fan Propulsion Systems Analysis


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    Aerospace Congress and Exposition ; 1982



    Publication date :

    1982-02-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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