Investigation of a supersonic-compressor rotor with turning to axial direction 1: rotor design and performance
Description: Report presenting an approximate, quasi-three-dimensional design procedure adapted to the design of high solidity, impulse-type supersonic compressors. The method is applied to a compressor rotor with a tip speed of 1600 feet per second in air, an inlet hub-tip radius ratio of 0.75, and an axial discharge relative to the rotor. Results regarding the overall performance, rotor-entrance conditions, static-pressure profiles, discharge conditions, and discharge surveys are provided.
Date: August 19, 1953
Creator: Tysl, Edward R.; Klapproth, John F. & Hartmann, Melvin J.
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Partner: UNT Libraries Government Documents Department