Transonic investigation of an axial-flow compressor rotor with a hub-tip ratio of 0.75 and blades having NACA A(sub 2)I(Sub 8b) mean lines
Description: Report presenting a blade-element analysis of a compressor rotor with blade sections with NACA A(sub 2)I(Sub 8b) mean lines and 65-series thickness distributions in Freon-12 gas. Results regarding blade loss, angle of attack associated with minimum loss, peak efficiencies, and comparison with other transonic rotors are provided.
Date: September 30, 1957
Creator: Bernot, Peter T. & Savage, Melvyn
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Partner: UNT Libraries Government Documents Department