A simplified mission analysis was performed to determine an optimum engine cycle for a 100-passenger VTOL transport with a range of 500 statute miles. The aircraft had a total of eight integral fan lift engines, three of which serve as cruise engines. Fan pressure ratio was varied from 1.2 to 1.3, overall pressure ratio from 7 to 13, and turbine inlet temperature from 2460 to 2860 R. Bypass ratio was selected to meet a 500-foot altitude flyover noise goal of 95 PNdB. Airplane gross weight and direct operating cost (DOC) were calculated. The lowest DOC of 1.82 cents per seat-mile was achieved with a fan pressure ratio of 1.3, overall pressure ratio of 12, and turbine inlet temperature of 2860 R. (Author)


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    Title :

    Preliminary Study of an Integral Fan Lift/Cruise Engine for a 100 Passenger VTOL Transport


    Contributors:

    Publication date :

    1973


    Size :

    36 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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