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Transonic steady- and unsteady-pressure measurements on a high-aspect-ratio supercritical-wing model with oscillating control surfacesA supercritical wing with an aspect ratio of 10.76 and with two trailing-edge oscillating control surfaces is described. The semispan wing is instrumented with 252 static orifices and 164 in situ dynamic-pressure gages for studying the effects of control-surface position and motion on steady- and unsteady-pressures at transonic speeds. Results from initial tests conducted in the Langley Transonic Dynamics Tunnel at two Reynolds numbers are presented in tabular form.
Document ID
19850009694
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Sandford, M. C. (NASA Langley Research Center Hampton, VA, United States)
Ricketts, R. H. (NASA Langley Research Center Hampton, VA, United States)
Cazier, F. W., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
December 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:81888
NASA-TM-81888
L-13964
Accession Number
85N18003
Funding Number(s)
PROJECT: RTOP 534-03-13-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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