Seymour Lieblein, George W. Lewis, Jr., Donald M. Sandercock
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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