The overall and blade-element performances and the aerodynamic design parameters of a transonic rotor with an aspect ratio of 6.5, designed to investigate the effects of aspect ratio on range and performance are presented. The rotor was designed for a total-pressure ratio of 1.53, an efficiency of 0.898, and a weight flow of 67.76 pounds per second.
Performance of a transonic compressor rotor with an aspect ratio of 6.5
01.06.1974
Sonstige
Keine Angabe
Englisch
Experimental investigation of a transonic compressor with high aspect ratio rotor design
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