Analysis of transonic rotor-blade passage loss with hot-wire anemometers
Description:
From Introduction: "This report presents data from measurements of the flow in a single-stage research compressor, which supports the model of reference 1. A calculated shock technique similar to that of reference 1 is incorporated with these experimental results. Another approach for estimating passage shock loss given a flow rate and blade geometry was reported in reference 2."
Date:
June 5, 1958
Creator:
Lewis, George W.; Tysl, Edward R. & Fessler, Theodore E.
Item Type:
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Partner:
UNT Libraries Government Documents Department