Performance of NACA eight-stage axial-flow compressor at simulated altitude /
J. Austin King and Owen W. Regan.

Description

Main Author

King, J. Austin.

Related Names

Regan, Owen W.
Aircraft Engine Research Laboratory.
United States. National Advisory Committee for Aeronautics.

Language(s)

English

Published

Washington, D.C. : National Advisory Committee for Aeronautics, [1944]

Subjects

Axial flow compressors > Axial flow compressors / Altitude, influence of.
Compressors > Compressors / Testing.
Axial flow compressors > Axial flow compressors / Performance.

Summary

An investigation has been conducted by the NACA to determine the design-performance characteristics of the NACA eight-stage axial-flow compressor and the effect of altitude on the performance. The compressor was tested at simulated altitudes of 50,000; 36,000; and 27,000 feet at rotor speeds corresponding to compressor Mach numbers of 0.80, 0.85, 0.90, and 0.95 wit varying air flow at each speed.

Note

Prepared at the Aircraft Engine Research Laboratory, Cleveland, Ohio.
Originally issued as NACA as Advance Confidential Report E4L21 (December 1944).
NACA Wartime Report E-5.

Physical Description

7, [10] p. : ill. ; 27 cm.

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