New Approach to Axial Compressor Cascade Testing Technique Langley Aeronautical Laboratory, NACA

Format:

Other

Author/Creator:

ERWIN, JOHN R., author.

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1950

Summary:

THE inadequacy of existing cascade data to satisfy 2-dimensional flow criteria is discussed in this paper.It presents the results of an investigation to determine the influence of aspect ratio, boundary-layer control by means of slots and porous surfaces, Reynold's number, and tunnel end-wall condition upon the performance of airfoils in cascades.A representative compressor blade section, the 65-(12) 10 airfoil, was tested in low-speed cascades of aspect ratios of one, two, and four with solid and with porous side walls.The authors report that 2-dimensional flow was established in porous-wall cascades of each of the three aspect ratios tested; the flow was not 2-dimensional in any of the solid-wall cascades

Notes:

Vendor supplied data

Publisher Number:

500179

Access Restriction:

Restricted for use by site license