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Wind-tunnel experiments on divergence of forward-swept wingsAn experimental study to investigate the aeroelastic behavior of forward-swept wings was conducted in the Langley Transonic Dynamics Tunnel. Seven flat-plate models with varying aspect ratios and wing sweep angles were tested at low speeds in air. Three models having the same planform but different airfoil sections (i.e., flat-plate, conventional, and supercritical) were tested at transonic speeds in Freon 12. Linear analyses were performed to provide predictions to compare with the measured aeroelastic instabilities which include both static divergence and flutter. Six subcritical response testing techniques were formulated and evaluated at transonic speeds for accuracy in predicting static divergence. Two "divergence stoppers" were developed and evaluated for use in protecting the model from structural damage during tests.
Document ID
19800020786
Document Type
Technical Publication (TP)
Authors
Ricketts, R. H. (NASA Langley Research Center Hampton, VA, United States)
Doggett, R. V., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
August 1, 1980
Subject Category
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number
L-13549
NASA-TP-1685
Funding Number(s)
PROJECT: RTOP 505-33-53-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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