Abstract
A series of calculations were carried out to obtain the performance of a six-, an eight-, and a 13-stage compressor, each designed for the same tip speed, to handle the same mass flow, and to develop a pressure ratio of 3.2. The simplified analysis was based on experimental cascade and single-stage studies. The effects of boundary-layer growth and distortion of the velocity profiles, which occur at the rear of multistage axial-flow compressors, were neglected.
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