Performance of high-pressure-ratio axial-flow compressor using highly cambered NACA 65-series blower blades at high Mach numbers

Voit, Charles H., Guentert, Donald C., Dugan, James F.
naca-rm-e50a09
1950


A complete stage of an axial-flow compressor was designed and built to investigate the possibility of obtaining a high pressure ratio with an acceptable efficiency through the use of the optimum combination of high blade loading and high relative inlet Mach number. Over-all stage performance was investigated over a range of flows at equivalent tip speeds of 418 to 836 feet per second. At design speed (836 ft/sec), a peak total-pressure ration of 1.445 was obtained with an adiabatic efficiency of 0.89. For design angle of attack at the mean radius, a total-pressure ratio of 1.392 was obtained.

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