NACA Research Memorandums

Performance data are presented for a transonic axial-flow compressor rotor designed to operate at a tip speed of 1300 ft/sec with maximum relative tip Mach number of 1.37. The compressor had an inlet diameter of 16 inches, a hub-tip diameter ratio of 0.5 and design specific weight flow of 31.1 (lb/sec/(sq ft frontal area). Experimental values of relative total-pressure-loss coefficient were considerably higher than the assumed values. This disparity, hub choking, and application of the simple radial-equilibrium concept are discussed. The data of this report are used to extend previously presented correlation plots of compressor design parameters to higher Mach numbers