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Supersonic aeroelastic instability results for a NASP-like wing modelTwo wing-alone wind-tunnel models were tested in the NASA Langley Unitary Plan Wind Tunnel facility to study the static divergence behavior of such configurations and to provide a data base for correlation with supersonic analytical predictions. One model had a four percent maximum thickness airfoil and the other had an eight-percent maximum thickness airfoil. The wing models had low aspect ratios and highly swept leading edges. Results show that decreasing airfoil thickness, moving the wing-pivot location upstream, or increasing the pitch-pivot stiffness have the beneficial effect of increasing the divergence dynamic pressures. The calculations accurately predicted the trend of experimental divergence dynamic pressure with Mach number.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Cole, Stanley R.
(NASA Langley Research Center Hampton, VA, United States)
Florance, James R.
(NASA Langley Research Center Hampton, VA, United States)
Thomason, Lee B.
(NASA Langley Research Center Hampton, VA, United States)
Spain, Charles V.
(NASA Langley Research Center Hampton, VA, United States)
Bullock, Ellen P.
(Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA(ASME)ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 34th and AIAA/ASME Adaptive Structures Forum, La Jolla, CA, Apr. 19-22, 1993, Technical Papers. Pt. 1 (A93-33876 1
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Report/Patent Number
AIAA PAPER 93-1369
Accession Number
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