NACA 65-series compressor rotor performance with varying annulus-area ratio, solidity, blade angle, and Reynolds number and comparison with cascade results /
Wallace M. Schultze, John R. Erwin, and George C. Ashby, Jr.

Description

Main Author: Schulze, Wallace M.
Related Names: Ashby, George C.
Erwin, John R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics.
Language(s): English
Published: Washington, D.C. : National Advisory Committee for Aeronautics, 1953.
Subjects: Reynolds number.
Compressors > Compressors / Performance.
Cascades (Fluid dynamics)
Axial flow compressors > Axial flow compressors / Blades.
Summary: A typical axial-flow compressor rotor using NACA 65-series compressor blades was tested at low speeds and its performance was measured over a range of quantity flow rates at several values of annulus-area ratio, blade-setting angle, solidity, and Reynolds number to compare with porouswall cascade results. The data obtained using varying annulus area were corrected to the two-dimensional-flow condition by two methods.
Note: "February 19, 1953."
Physical Description: 62 p. : ill. ; 27 cm.
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