Investigation of 10-stage axial flow X24C-2 compressor. : I Performance at inlet pressure of 21 inches mercury absolute and inlet temperature of 538 degree

Schum, Harold J., Buckner, Howard A.

An investigation is being conducted to determine the performance of the 10-stage axial-flow compressor from the X24C-2 turbojet engine. The performance of the compressor at an inlet pressure of 21 inches of mercury absolute and an inlet temperature of 538 degrees R for percentages of equivalent design speed from 30 to 100 has been determined.

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