Performance of NACA Eight-stage Axial-flow Compressor Designed on the Basis of Airfoil Theory

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Summary: The NACA has conducted an investigation to determine the performance that can be obtained from a multistage axial-flow compressor based on airfoil research. A theory was developed; an eight-stage axial-flow compressor was designed, constructed, and tested. The performance of the compressor was determined for speeds from 5000 to 14,000 r.p.m with varying air flow at each speed. Most of the tests were made with air at room temperature. The performance was determined in accordance with the Committee's recommended procedure for testing superchargers. The expected performance was obtained, showing that a multistage compressor of high efficiency can be designed by the application of airfoil theory.
Collection: NASA Technical Reports Server (NTRS) Collection.
Note: Document ID: 19930091837.
Accession ID: 93R21127.
NACA-TR-758.
Terms of Use and Reproduction: No Copyright.

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