27th Congress of International Council of the Aeronautical Sciences, 19 - 24 September 2010, Nice, France
Paper ICAS 2010-9.6.1

REDUCED UNCERTAINTIES IN THE ROBUST FLUTTER ANALYSIS OF THE AEROSTRUCTURES TEST WING

C. -G. Pak, S. -F. Lung
NASA Dryden, USA

Keywords: aerostructures test wing, flutter margin, structural dynamic model tuning, test validated structural dynamic model, uncertainties

The primary objective of this study is to reduce uncertainties in the structural dynamic FE model of the ATW2 to increase the safety of flight. Discrepancies are common between the test data and numerical results. However, the FE model can be fine tuned through the use of GVT data.

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