Effect of Mach number on the flow and application of compressibility corrections in a two-dimensional subsonic-transonic compressor cascade having varied porous-wall suction at the blade tips

William B. Briggs
naca-tn-2649
Mar 1952


A cascade of 65-(12)10 compressor blades was tested at one geometric getting over a range of inlet Mach number from 0.12 to 0.89. Two groups of data are presented and compared: the first from the cascade operating conventionally with no boundary-layer control, and the second with the boundary layer controlled by a combination of upstream slot suction and porous-wall suction at the blade tips.

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