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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    Title :

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


    Contributors:
    L. Reid (author) / E. R. Tysl (author)

    Publication date :

    1974


    Size :

    69 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






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