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. (Author)


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    Titel :

    Performance of a Transonic Compressor Rotor with an Aspect Ratio of 6.5


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

    Erscheinungsdatum :

    1974


    Format / Umfang :

    69 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch