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Effect of milling machine roughness and wing dihedral on the supersonic aerodynamic characteristics of a highly swept wingAn experimental investigation was conducted to assess the effect of surface finish on the longitudinal and lateral aerodynamic characteristics of a highly-swept wing at supersonic speeds. A study of the effects of wing dihedral was also made. Included in the tests were four wing models: three models having 22.5 degrees of outboard dihedral, identical except for surface finish, and a zero-dihedral, smooth model of the same planform for reference. Of the three dihedral models, two were taken directly from the milling machine without smoothing: one having a maximum scallop height of 0.002 inches and the other a maximum scallop height of 0.005 inches. The third dihedral model was handfinished to a smooth surface. Tests were conducted in Test Section 1 of the Unitary Plan Wind Tunnel at NASA-Langley over a range of Mach numbers from 1.8 to 2.8, a range of angle of attack from -5 to 8 degrees, and at a Reynolds numbers per foot of 2 x 10(6). Selected data were also taken at a Reynolds number per foot of 6 x 10(6). Drag coefficient increases, with corresponding lift-drag ratio decreases were the primary aerodynamic effects attributed to increased surface roughness due to milling machine grooves. These drag and lift-drag ratio increments due to roughness increased as Reynolds number increased.
Document ID
19890015746
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Darden, Christine M.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
August 1, 1989
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:2918
NASA-TP-2918
L-16546
Accession Number
89N25117
Funding Number(s)
PROJECT: RTOP 505-69-01-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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