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Framework for T-tail flutter analysis

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dc.contributor.author Van Zyl, Louwrens H
dc.date.accessioned 2011-08-10T13:55:46Z
dc.date.available 2011-08-10T13:55:46Z
dc.date.issued 2011-06
dc.identifier.citation Van Zyl, L.H. 2011. Framework for T-tail flutter analysis. International Forum on Aeroelasticity and Structural Dynamics 2011 (IFASD2011), Paris, France, 26-30 June 2011, pp. 14 en_US
dc.identifier.uri http://hdl.handle.net/10204/5123
dc.description International Forum on Aeroelasticity and Structural Dynamics 2011 (IFASD2011), Paris, France, 26-30 June 2011 en_US
dc.description.abstract The flutter analysis of T-tail aircraft poses challenges that are unique to this configuration, including the fact that the unsteady air loads are dependent on the steady load distribution and static deformation of the aircraft. In particular, the trim load on the horizontal stabilizer and the static deformation of the horizontal stabilizer, an induced dihedral effect, are significant. These effects are now well understood and accurate analyses can be made for a given set of conditions of incidence angle, elevator deflection and deformation. This paper considers the process required to perform the flutter analyses of a T-tailed aircraft. en_US
dc.language.iso en en_US
dc.relation.ispartofseries Workflow;6759
dc.subject T-tail en_US
dc.subject Flutter en_US
dc.title Framework for T-tail flutter analysis en_US
dc.type Conference Presentation en_US
dc.identifier.apacitation Van Zyl, L. H. (2011). Framework for T-tail flutter analysis. http://hdl.handle.net/10204/5123 en_ZA
dc.identifier.chicagocitation Van Zyl, Louwrens H. "Framework for T-tail flutter analysis." (2011): http://hdl.handle.net/10204/5123 en_ZA
dc.identifier.vancouvercitation Van Zyl LH, Framework for T-tail flutter analysis; 2011. http://hdl.handle.net/10204/5123 . en_ZA
dc.identifier.ris TY - Conference Presentation AU - Van Zyl, Louwrens H AB - The flutter analysis of T-tail aircraft poses challenges that are unique to this configuration, including the fact that the unsteady air loads are dependent on the steady load distribution and static deformation of the aircraft. In particular, the trim load on the horizontal stabilizer and the static deformation of the horizontal stabilizer, an induced dihedral effect, are significant. These effects are now well understood and accurate analyses can be made for a given set of conditions of incidence angle, elevator deflection and deformation. This paper considers the process required to perform the flutter analyses of a T-tailed aircraft. DA - 2011-06 DB - ResearchSpace DP - CSIR KW - T-tail KW - Flutter LK - https://researchspace.csir.co.za PY - 2011 T1 - Framework for T-tail flutter analysis TI - Framework for T-tail flutter analysis UR - http://hdl.handle.net/10204/5123 ER - en_ZA


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