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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