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dc.contributor.authorStettner, Martinen_US
dc.contributor.authorSchrage, Daniel P.en_US
dc.contributor.authorPeters, D. A. (David A.)en_US
dc.date.accessioned2005-05-26T14:05:17Z
dc.date.available2005-05-26T14:05:17Z
dc.date.issued1994-02en_US
dc.identifier.urihttp://hdl.handle.net/1853/6413
dc.descriptionPresented at the American Helicopter Society Aeromechanics Specialists Meeting, San Francisco, CA, January 19-21, 1994.en_US
dc.description.abstractThe Peters/He Finite State Wake Model is described in its application to fixed wing aerolasticity. Expressions for coupling this model with a wing, aerodynamically represented by a flat plate with a trailing edge flap, are developed, and fidelity issues are discussed. An application is presented where the wing/wake system is coupled to a proprotor model. The effects of unsteady wing aerodynamics on damping of this system are investigated. It is found that wake effects are small as a result of generally low damping levels in the system due to wing aerodynamic damping.en_US
dc.format.extent156963 bytes
dc.format.mimetypeapplication/pdf
dc.language.isoen_USen_US
dc.publisherGeorgia Institute of Technologyen_US
dc.relation.ispartofseriesASDL;AHS-0194-66en_US
dc.subjectTilt rotor aircraften_US
dc.subjectAerodynamicsen_US
dc.subjectRotary wingsen_US
dc.subjectAeroelasticityen_US
dc.subjectControl surfacesen_US
dc.subjectUnsteady aerodynamicsen_US
dc.subjectWakesen_US
dc.subjectDampingen_US
dc.titleApplication of a State-Space Wake Model to Tiltrotor Wing Unsteady Aerodynamicsen_US
dc.typePaper


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