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dc.contributor.advisorMedina, Ricardoen_US
dc.contributor.authorWheeler, Philip Curtisen_US
dc.date.accessioned2004-06-04T05:25:45Z
dc.date.available2004-06-04T05:25:45Z
dc.date.issued2004-04-30en_US
dc.identifier.urihttp://hdl.handle.net/1903/1375
dc.description.abstractThis thesis examines the dynamic instability known as flutter using a two-degree-of-freedom airfoil section model in both quasi-steady and unsteady flow. It explains the fundamental forces and moments involved in the bending-torsion flutter of an airfoil section, and demonstrates a solution method for determining the critical flutter frequency and speed for both flow cases. Additionally, through the use of a programmed Mathcad 11 worksheet, it evaluates the flutter characteristics of six example sections, illustrating the effects of the elastic, inertial and aerodynamic properties of an airfoil section. For each section, a parametric study of the effect of the section Center of Gravity position along the section chord is performed. The flutter frequency and speed are calculated using both quasi-steady and unsteady aerodynamic forces and moments, and the results compared. Software used was MathSoft Mathcad 11, Microsoft Word and Intergraph Smart Sketch LE.en_US
dc.format.extent1664709 bytes
dc.format.mimetypeapplication/pdf
dc.language.isoen_US
dc.titleAN EXPLICATION OF AIRFOIL SECTION BENDING-TORSION FLUTTERen_US
dc.typeThesisen_US
dc.relation.isAvailableAtDigital Repository at the University of Marylanden_US
dc.relation.isAvailableAtUniversity of Maryland (College Park, Md.)en_US
dc.contributor.departmentCivil Engineeringen_US
dc.subject.pqcontrolledEngineering, Civilen_US
dc.subject.pqcontrolledEngineering, Aerospaceen_US
dc.subject.pquncontrolledFlutteren_US
dc.subject.pquncontrolledAeroelasticityen_US
dc.subject.pquncontrolledStructural Dynamicsen_US


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