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Transonic Loads Characteristics of a 3-Percent-Thick 60 deg Delta-Wing-BodyAn investigation has been made in the Langley 16-foot transonic tunnel to determine the aerodynamic loading characteristics of a 3-percent-thick, aspect-ratio - 2.06, 60 deg delta-wing-body combination. The Mach number range was from 0.80 t o 1.05 and the average Reynolds number based on wing mean aerodynamic chord was 10 x 10(exp 6). The angle-of-attack range was from 0 deg to 26 deg but was limited at the highest Mach numbers by tunnel drive power. Pressure distributions, spanwise loadings, integrated wing coefficients, and tabulated pressure coefficients are presented for the range of Mach numbers and angles of attack. The results indicate that a free leading-edge separation vortex is the dominant flow-field phenomenon at all Mach numbers and that, consequently, there are only slight changes in the spanwise loadings with Mach number. There is a slight outboard shift in center of pressure with an increase in Mach number. The chord-wise position of the center of pressure varies from 46 t o 55 percent of the mean aerodynamic chord when the Mach number i s increased from 0.80 to l.05.
Document ID
20040008224
Acquisition Source
Langley Research Center
Document Type
Other - NASA Technical Note (TN)
Authors
Swihart, John M.
(NASA Langley Research Center Hampton, VA, United States)
Foss, Willard E., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 21, 2013
Publication Date
May 1, 1961
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
L-1543
NASA-TN-D-830
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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