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
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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