A high-solidity low-aspect-ratio transonic rotor with an inlet hub-tip ratio of 0.52 was investigated experimentally. The rotor developed a total-pressure tatio of 1.93 and an efficiency of 92 percent at an equivalent wheel tip speed of 1036 feet per second. The feasibility of using this rotor as a component of an inlet stage of an axial-flow compressor was investigated.
Performance of a High-solidity High-pressure-ratio Transonic Rotor
1955-11-08
Miscellaneous
No indication
English
AIAA-2005-1014 CFD STUDIES ON HIGH PRESSURE RATIO TRANSONIC ROTOR BLADE
British Library Conference Proceedings | 2005
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