Experimental investigation of an axial flow compressor inlet stage operating at transonic relative inlet Mach numbers I : over-all performance of stage with transonic rotor and subsonic stators up to rotor relative inlet Mach number of 1.1

Seymour Lieblein, George W. Lewis, Jr., Donald M. Sandercock
naca-rm-e52a24
Mar 1952


An axial-flow compressor inlet stage having a maximum rotor relative inlet Mach number of 1.1 was designed, constructed, and investigated. The rotor was designed for a high axial inlet velocity, no inlet guide vanes, and a tip speed of 1000 feet per second. The hub-tip ratio at the rotor inlet was 0.525. The stators were designed for current limiting values of stator inlet Mach number.

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