Hedgepeth, John Mills2014-03-142014-03-141957-03-05etd-11072012-040239http://hdl.handle.net/10919/45527The panel flutter analysis presented herein has been restricted to the problem of an isolated simply supported plate of uniform thickness. The same type of analysis can be applied, however, to other panel configurations. Clamped panels, integrally stiffened panels, arrays of panels, end others should be amenable to treatment by the model approach based on the static aerodynamic approximation.59 leavesBTDapplication/pdfenIn CopyrightLD5655.V855 1957.H423Aerodynamics, SupersonicFlutter (Aerodynamics)Thesishttp://scholar.lib.vt.edu/theses/available/etd-11072012-040239/