A high-solidity low-aspect-ratio transonic rotor with an inlet hub-tip ratio of 0.52 was investigated experimentally. The rotor developed a total-pressure tatio of 1.93 and an efficiency of 92 percent at an equivalent wheel tip speed of 1036 feet per second. The feasibility of using this rotor as a component of an inlet stage of an axial-flow compressor was investigated.


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    Title :

    Performance of a High-solidity High-pressure-ratio Transonic Rotor


    Contributors:

    Publication date :

    1955-11-08


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English





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