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Aerodynamic characteristics of two-dimensional wing configurations at angles of attack near -90 degWind tunnel tests were conducted to determine the drag of two-dimensional wing sections operating in a near-vertical flow condition. Various leading- and trialing-edge configurations, including plain flaps of 25, 30, and 35% chord were tested at angles of attack from -75 to -105 deg. Reynolds numbers examined ranged from approximately 0.6 x 10 to the 6th power to 1.4 x 10 to the 6th power. The data were obtained using a wind tunnel force and moment balance system and arrays of chordwise pressure orifices. The results showed that significant reductions in drag, beyond what would be expected by virtue of the decreased frontal area, were obtainable with geometries that delayed flow separation. Rapid changes in drag with angle of attack were noted for many configurations. The results, however, were fairly insensitive to Reynolds number variations. Drag values computed from the pressure data generally agreed with the force data within 2%.
Document ID
19870005749
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Maisel, Martin (NASA Ames Research Center Moffett Field, CA, United States)
Laub, Georgene (NASA Ames Research Center Moffett Field, CA, United States)
Mccroskey, W. J. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 5, 2013
Publication Date
December 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:88373
USAAVSCOM-TM-86-A-8
NASA-TM-88373
A-86427
AD-A178696
Accession Number
87N15182
Funding Number(s)
PROJECT: RTOP 532-06-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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