Suppressing aeroelastic instability using broadband passive targeted energy transfers, part 2: Experiments

Lee, YS; Kerschen, G; Michael McFarland, D; Joel Hill, W; Nichkawde, C; Strganac, TW; Bergman, LA; Vakakis, AF

dc.contributor.author	Lee, YS	en
dc.contributor.author	Kerschen, G	en
dc.contributor.author	Michael McFarland, D	en
dc.contributor.author	Joel Hill, W	en
dc.contributor.author	Nichkawde, C	en
dc.contributor.author	Strganac, TW	en
dc.contributor.author	Bergman, LA	en
dc.contributor.author	Vakakis, AF	en
dc.date.accessioned	2014-03-01T01:27:21Z
dc.date.available	2014-03-01T01:27:21Z
dc.date.issued	2007	en
dc.identifier.issn	0001-1452	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/18412
dc.subject.classification	Engineering, Aerospace	en
dc.subject.other	Cycle oscillation	en
dc.subject.other	Nonlinear energy sink	en
dc.subject.other	Nonlinear springs	en
dc.subject.other	Airfoils	en
dc.subject.other	Degrees of freedom (mechanics)	en
dc.subject.other	Energy transfer	en
dc.subject.other	Speed control	en
dc.subject.other	Aerodynamics	en
dc.title	Suppressing aeroelastic instability using broadband passive targeted energy transfers, part 2: Experiments	en
heal.type	journalArticle	en
heal.identifier.primary	10.2514/1.28300	en
heal.identifier.secondary	http://dx.doi.org/10.2514/1.28300	en
heal.language	English	en
heal.publicationDate	2007	en
heal.abstract	This paper presents experimental results corroborating the analysis developed in the companion paper, Part 1 (Lee, Y., Vakakis, A., Bergman, L., McFarland, M., and Kerschen G., ""Suppression Aeroelastic Instability Using Broadband Passive Targeted Energy Transfers, Part 1: Theory,"" AIAA Journal, Vol. 45, No. 3, 2007, pp. 693-711), and demonstrates that a nonlinear energy sink can improve the stability of an aeroelastic system. The nonlinear energy sink was, in this case, attached to the heave (plunge) degree of freedom of a rigid airfoil which was supported in a low-speed wind tunnel by nonlinear springs separately adjustable in heave and pitch. This airfoil was found to exhibit a limit cycle oscillation at flow speeds above the critical (""flutter"") speed of 9.5 m/s, easily triggered by an initial heave displacement After attachment of a single degree of freedom, essentially nonlinear energy sink to the wing, the combined system exhibited improved dynamic response as measured by the reduction or elimination of limit cycle oscillation at flow speeds significantly greater than the wing's critical speed. The design, application, and performance of the nonlinear energy sink are described herein, and the results obtained are compared to analytical predictions. The physics of the interaction of the sink with the wing is examined in detail.	en
heal.publisher	AMER INST AERONAUT ASTRONAUT	en
heal.journalName	AIAA Journal	en
dc.identifier.doi	10.2514/1.28300	en
dc.identifier.isi	ISI:000250346900002	en
dc.identifier.volume	45	en
dc.identifier.issue	10	en
dc.identifier.spage	2391	en
dc.identifier.epage	2400	en