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Wind tunnel turning vanes of modern designRehabilitation of the Altitude Wind Tunnel includes the need for new corner turning vanes to match its upgraded performance. The design and experimental performance results from a 0.1-full scale model of the highest speed corner (M = 0.35) are presented and discussed along with some two dimensional inviscid analyses of two vaned corners. With a vane designed by an inverse two dimensional technique, the overall corner loss was about 12% of the inlet dynamic pressure of which about 4% was caused by vane skin friction. Comparable values with a conventionally designed circular arc vane were about 14% overall with about 7% due to skin friction.
Document ID
19860002772
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gelder, T. F. (NASA Lewis Research Center Cleveland, OH, United States)
Moore, R. D. (NASA Lewis Research Center Cleveland, OH, United States)
Sanz, J. M. (NASA Lewis Research Center Cleveland, OH, United States)
Mcfarland, E. R. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1985
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
E-2775
NASA-TM-87146
NAS 1.15:87146
AIAA PAPER 86-0044
Meeting Information
Meeting: Aerospace Sci. Meeting
Location: Reno, NV
Country: United States
Start Date: January 6, 1986
End Date: January 8, 1986
Sponsors: AIAA
Accession Number
86N12239
Funding Number(s)
PROJECT: RTOP 505-62-3A
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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