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Wind tunnel tests of high-lift systems for advanced transports using high-aspect-ratio supercritical wingsThe wind tunnel testing of an advanced technology high lift system for a wide body and a narrow body transport incorporating high aspect ratio supercritical wings is described. This testing has added to the very limited low speed high Reynolds number data base for this class or aircraft. The experimental results include the effects on low speed aerodynamic characteristics of various leading and trailing edge devices, nacelles and pylons, ailerons, and spoilers, and the effects of Mach and Reynolds numbers.
Document ID
19840020673
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Allen, J. B. (Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Oliver, W. R. (Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Spacht, L. A. (Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Date Acquired
September 4, 2013
Publication Date
July 1, 1982
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-3523
ACEE-17-FR-1608
NAS 1.26:3523
Accession Number
84N28742
Funding Number(s)
CONTRACT_GRANT: NAS1-15327
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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