Component and over-all performance evaluation of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers
Description: Report presenting an investigation in an altitude test chamber to evaluate the performance of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers. Reducing the engine inlet Reynolds number resulted in a reduction of corrected air flow and compressor efficiency but did not affect the compressor pressure ratio at a given corrected engine speed.
Date: July 10, 1952
Creator: Walker, Curtis L.; Huntley, S. C. & Braithwaite, W. M.
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Partner: UNT Libraries Government Documents Department