A transonic compressor stage designed for a reduced loading in the tip region of the rotor blades was tested with and without inlet radial distortion. Three levels of tip radial distortion and one level of hub radial distortion produced by inlet screens were imposed on the inlet flow. The rotor was 50 centimeters in diameter and designed for an operating tip speed of 420 meters per second. For clean inlet flow, overall per-formance data is presented at 60, 70, 80, 90, and 100 percent of equivalent design speed. With distortion, overall performance data is presented at 70 and 100 percent of equivalent design speed. Blade-element performance parameters are presented for selected operating conditions at 100 percent design speed.
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