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Analytical design of a contoured wind-tunnel liner for supercritical testingThe present analytical design procedure is being developed in order to determine the shape of a contoured nonporous wind tunnel liner for use in the Ames 12-foot pressure wind tunnel test of a large chord, laminar flow control, swept wing panel which has a supercritical airfoil section. This procedure is applicable to the two-dimensional streamlined tunnel problem wall shape with that found experimentally.
Document ID
19790011822
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Newman, P. A. (NASA Langley Research Center Hampton, VA, United States)
Anderson, E. C. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1978
Publication Information
Publication: Advanced Technol. Airfoil Res., Vol. 1, Pt. 2
Subject Category
Research And Support Facilities (Air)
Accession Number
79N19993
Funding Number(s)
CONTRACT_GRANT: NAS1-14517
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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IDRelationTitle19790011818Collected WorksAdvanced technology airfoil research, volume 1, part 2
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