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Measured transonic unsteady pressures on an energy efficient transport wing with oscillating control surfacesHighlight results are presented from subsonic and transonic pressure measurement studies conducted in the Langley Transonic Dynamics Tunnel on a supercritical wing model representative of an energy efficient transport design. Steady- and unsteady-pressure data were acquired on the upper and lower wing surface at an off-design Mach number of 0.60 and at the design Mach number of 0.78, for a Reynolds number of 2.2 x 10(6) (based on the wing average chord). The model configuration consisted of a sidewall-Mounted half-body fuselage and a semi-span wing with an aspect ratio of 10.76, a leading-edge sweepback angle of 28.8 degrees, and supercritical airfoil sections. The wing is instrumented with 252 static pressure orifices and 164 dynamic pressure gages. Model test variables included wing angle of attack, control-surface mean deflection angle, control-surface oscillating deflection angle and frequency, and phasing between oscillating leading-edge and trailing-edge controls when used together.
Document ID
19840019595
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cazier, F. W., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Watson, J. J.
(NASA Langley Research Center Hampton, VA, United States)
Doggett, R. V., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Sandford, M. C.
(NASA Langley Research Center Hampton, VA, United States)
Ricketts, R. H.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
December 1, 1981
Publication Information
Publication: Advan. Aerodyn.: Selected NASA Res.
Subject Category
Aerodynamics
Accession Number
84N27663
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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