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A new design concept for indraft wind-tunnel inlets with application to the national full-scale aerodynamic complexThe present inlet design concept for an indraft wind tunnel, which is especially suited to applications for which a specific test section flow quality is required with minimum inlet size, employs a cascade or vaneset to control flow at the inlet plane, so that test section total pressure variation is minimized. Potential flow panel methods, together with empirical pressure loss predictions, are used to predict inlet cascade performance. This concept has been used to develop an alternative inlet design for the 80 x 120-ft wind tunnel at NASA Ames Research Center. Experimental results show that a short length/diameter ratio wind tunnel inlet furnishing atmospheric wind isolation and uniform test section flow can be designed.
Document ID
19870011573
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Ross, James C. (NASA Ames Research Center Moffett Field, CA, United States)
Olson, Lawrence E. (NASA Ames Research Center Moffett Field, CA, United States)
Meyn, Larry A. (NASA Ames Research Center Moffett Field, CA, United States)
Vanaken, Johannes M. (Kansas Univ. Center for Research, Inc., Lawrence, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1986
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
NAS 1.15:88226
NASA-TM-88226
A-85392
Accession Number
87N21006
Funding Number(s)
PROJECT: RTOP 505-31-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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