Theoretical effect of inlet hub-tip-radius ratio and design specific mass flow on design performance of axial-flow compressors

Chung-Hua Wu, John T. Sinnette, Robert E. Forrette
naca-tn-2068
Apr 1950


An analysis was made of the effect at design condition of inlet hub-tip-radius ratio and mass flow per unit frontal area on the allowable rotor-tip speed, pressure ratio, and power input per unit frontal area of multistage axial-flow compressors employing approximately symmetrical velocity diagrams at all radii, constant total enthalpy along the radius, a maximum Mach number of 0.8 for all stages, and a prescribed empirical turning limitation.

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