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Pressure Distributions from Subsonic Tests of a NACA 0012 Semispan Wing ModelAn unswept, semispan wing model incorporating a NACA 0012 airfoil section was tested in the Langley 14- by 22-Foot Subsonic Tunnel. This report contains pressure data which document effects of wing configuration and free-stream conditions on wing pressure distributions. The untwisted wing incorporated a full-span, leading-edge Krueger flap and a full-span, single-slotted trailing-edge flap. The trailing-edge flap was tested at a deflection angle of 40 degrees and the Krueger flap at a deflection of 55 degrees. Three wing configurations were tested: cruise, trailing-edge flap only, and Knueger flap and trailing-edge flap deployed. Tests were conducted at free-stream dynamic pressures of 15, 30 and 60 psf, with corresponding chord Reynolds numbers of 1.22 to 2.11 million and Mach numbers of 0.12 to 0.20. Angles of attack presented range from 0 to 20 degrees, depending on wing configuration. The data are presented without analysis.
Document ID
19960001217
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Applin, Zachary T.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1995
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-110148
NAS 1.15:110148
Accession Number
96N11224
Funding Number(s)
PROJECT: RTOP 538-05-14-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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