Results of experiments in National Research Council 10×20-ft VTOL propulsion tunnel on unassisted cowled intakes in inclined flow; 10 intake configurations incorporating common centerbody and with various lip profiles were investigated over range of freestream to intake velocity ratio up to 2.0 and cross-flow angle from 0 to 165°; results are presented in terms of range of cross-flow conditions, for which intake pressure loss is small, together with approximate loss data under conditions characterized by extensive flow separation; preliminary data on effect of distorted intake flow on fan performance are included.


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    Title :

    Experimental investigation of inclined compressor inflow


    Additional title:

    Can Aeronautics Space J


    Contributors:


    Publication date :

    1966


    Size :

    18 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English