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Transonic unsteady airloads on an energy efficient transport wing with oscillating control surfacesAn aspect-ratio 10.8 supercritical wing with oscillating control surfaces is described. The wing is instrumented with 252 static orifices and 164 in situ dynamic pressure transducers for studying the effects of control surface deflection on steady and unsteady pressures at transonic speeds. Selected results from initial wind-tunnel tests conducted in the Langley Transonic Dynamics Tunnel are discussed. Unsteady pressure results are presented for two trailing-edge control surfaces oscillating separately at the design Mach number of 0.78. Some experimental results are compared with analytical results obtained by using linear lifting-surface theory.
Document ID
19800050871
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
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)
Cunningham, H. J. (NASA Langley Research Center Structures and Dynamics Div., Hampton, Va., United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 80-0738
Meeting Information
Meeting: Structures, Structural Dynamics, and Materials Conference
Location: Seattle, WA
Start Date: May 12, 1980
End Date: May 14, 1980
Accession Number
80A35041
Distribution Limits
Public
Copyright
Other

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