Investigation of an axial-flow compressor rotor having NACA high-speed blade sections (A(sub 2)I(sub 8b) series) at mean radius relative inlet Mach numbers up to 1.13
Description: Report presenting the results of testing on a high-pressure-ratio, axial-flow compressor rotor designed to operate efficiently at high speeds. High flows are needed to increase engine thrust without increasing engine front area. Results regarding the overall total-pressure ratio and adiabatic efficiency, effect of angle of attack on efficiency, determination of the effect of mean radius rotor inlet Mach number and Reynolds number on turning angle, and other information about ideal operation of the rotor are provided.
Date: November 30, 1953
Creator: Savage, Melvyn; Erwin, John R. & Whitley, Robert P.
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Partner: UNT Libraries Government Documents Department