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dc.contributor.advisorKahn, Charles H.
dc.contributor.authorParcells, Paul Whitney
dc.date.accessioned2012-08-29T23:36:36Z
dc.date.available2012-08-29T23:36:36Z
dc.date.issued1967-12
dc.identifier.urihttp://hdl.handle.net/10945/13261
dc.description.abstractThe validity of conventional skin and stringer type analyses is verified experimentally for a thick milled skin aircraft structure. The accuracy of solution is evaluated by comparing the strain energies in a mathematical model to that obtained experimentally from a wing panel of a high performance aircraft. Results indicate that the conventional methods of a skin-stringer/matrix force approach are valid for a thick milled skin aircraft structure of this type provided the panel loading is neither severe nor concentrated. Additionally the grid elements chosen must be small enough to preculde any gross averaging errorsen_US
dc.description.urihttp://www.archive.org/details/theoreticalempir00parc
dc.format.extent76 p.: ill.en_US
dc.language.isoen_US
dc.publisherMonterey, California. U.S. Naval Postgraduate Schoolen_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.en_US
dc.titleTheoretical and empirical analyses of thick skinned swept wing panelsen_US
dc.typeThesisen_US
dc.description.serviceLieutenant, United States Navyen_US
etd.thesisdegree.nameM.S. in Aeronautical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAeronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US


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