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Investigation of transonic region of high dynamic response encountered on an elastic supercritical wingUnsteady aerodynamic data were measured on an aspect ratio 10.3 elastic supercritical wing while undergoing high dynamic response above a Mach number of 0.90. These tests were conducted in the NASA Langley Transonic Dynamics Tunnel. A previous test of this wing predicted an unusual instability boundary based on subcritical response data. During the present test no instability was found, but an angle of attack dependent narrow Mach number region of high dynamic wing response was observed over a wide range of dynamic pressures. The effect on dynamic wing response of wing angle of attack, static outbound control surface deflection and a lower surface spanwise fence located near the 60 percent local chordline was investigated. The driving mechanism of the dynamic wing response appears to be related to chordwise shock movement in conjunction with flow separation and reattachment on both the upper and lower surfaces.
Document ID
19870010803
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Seidel, David A. (NASA Langley Research Center Hampton, VA, United States)
Eckstrom, Clinton V. (NASA Langley Research Center Hampton, VA, United States)
Sandford, Maynard C. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1987
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 87-0735-CP
NASA-TM-89121
NAS 1.15:89121
Accession Number
87N20236
Funding Number(s)
PROJECT: RTOP 505-63-21-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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