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.
Experimental investigation of inclined compressor inflow
Can Aeronautics Space J
Canadian Aeronautics and Space Journal ; 12 , n 2
1966
18 pages
Article (Journal)
English
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Experimental investigation of water inflow and reaction in propeller
Engineering Index Backfile | 1936
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