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Wind-tunnel measurements of aerodynamic load distribution on an NASA supercritical-wing research airplane configurationWind tunnel tests have been conducted on a research airplane model with an NASA supercritical wing to define the general character of the flow over the wing and to aid in structural design of the full scale airplane. Pressure measurements were made at Mach numbers from 0.25 to 1.30 for sideslip angles from -2.50 deg to 2.50 deg over a moderate range of angles of attack and dynamic pressures. Except for representative figures, the results are presented in tabular form without detailed analysis.
Document ID
19780016136
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Harris, C. D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
February 1, 1972
Subject Category
Aerodynamics
Report/Patent Number
L-7982
NASA-TM-X-2469
Accession Number
78N24079
Funding Number(s)
PROJECT: RTOP 742-73-01-14
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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