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Solution of the Flutter Eigenvalue Problem with Mixed Structural/Aerodynamic Uncertainty
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.ORCID iD: 0000-0003-2391-641X
2011 (English)In: Journal of Aircraft, ISSN 0021-8669, Vol. 48, no 1, 343-348 p.Article in journal (Refereed) Published
Abstract [en]

The solution of the flutter eigenvalue problem with mixed structural/aerodynamic uncertainty was examined. A delta-wing wind-tunnel model was used as a test case. The model had a simple structural design and was made of glass-fiber and carbon-fiber composite materials. It had a semispan of 0.88 m and mean chord of 0.70m and was mounted vertically in the low-speed wind tunnel L2000. The numerical analysis was based on a NASTRAN model with shell elements for the wing, mass elements for the missile, and aerodynamic panels for doublet-lattice aerodynamic loads. The relatively stiff missile was modeled as a rigid body attached to the wing tip. The nominal eigenvalue was always an interior point of the corresponding eigenvalue set. A parameter sweep taking only aerodynamic uncertainty into account was performed by solving the eigenvalue problem for a set of parameter values. The eigenvalue sets based on one patch and seven patches, respectively, showed only slight difference.

Place, publisher, year, edition, pages
2011. Vol. 48, no 1, 343-348 p.
National Category
Mechanical Engineering
URN: urn:nbn:se:kth:diva-31621DOI: 10.2514/1.C031204ISI: 000287227200034ScopusID: 2-s2.0-79551666217OAI: diva2:406057
QC 20110324Available from: 2011-03-24 Created: 2011-03-21 Last updated: 2011-03-24Bibliographically approved

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Borglund, DanRingertz, Ulf
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