Investigation carried out in test blower; performance of four sets of rotor blades, designed to set up free vortex flow and operating with design pitch-section lift coefficients from 0.31 to 0.99, was studied by making surveys of yaw angles and pressures; tests made in single-stage test blower at Langley Memorial Aeronautical Laboratory of NACA.


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    Title :

    Performance of axial-flow fan and compressor blades designed for high loadings


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:


    Publication date :

    1947


    Size :

    13 pages


    Remarks:

    18 Supp Plates


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :