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.
naca-rm-e7g11
1947


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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