Abstract
This paper describes a method of correlating wind-tunnel tests on axial-flow-compressor cascades. The use and construction of two charts for the NACA four-digit airfoil series are described. The charts relate the three cascade quantities; camber, solidity, and stagger angle with two flow angles; the entrance angle, and the turning angle, for low Mach numbers. When four of these five variables are given, the fifth is determined. A simple computation procedure to correct the solution for a high subsonic Mach number is given. The profile drag does not enter the correlation scheme directly but an approximate guide is indicated on the charts.
Issue Section:
Research Papers
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