The overall and blade-element performances and the aerodynamic design parameters of a transonic rotor with an aspect ratio of 6.5, designed to investigate the effects of aspect ratio on range and performance are presented. The rotor was designed for a total-pressure ratio of 1.53, an efficiency of 0.898, and a weight flow of 67.76 pounds per second.


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    Titel :

    Performance of a transonic compressor rotor with an aspect ratio of 6.5


    Beteiligte:
    Reid, L. (Autor:in) / Tysl, E. R. (Autor:in)

    Erscheinungsdatum :

    01.06.1974


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :




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