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dc.contributor.advisorCollins, Daniel J.
dc.contributor.authorGavito, Valentin Francisco Jr.
dc.dateDecember 1976
dc.date.accessioned2012-11-16T18:47:40Z
dc.date.available2012-11-16T18:47:40Z
dc.date.issued1976-12
dc.identifier.urihttp://hdl.handle.net/10945/17777
dc.description.abstractThe finite element method is applied to The two-dimensional, inviscid, compressible radial equilibrium equation for axial compressors. Isoparametric elements are used along with three-point Gaussian integration for stiffness matrix evaluation. The radial equilibrium equation is put into quasi-harmonic form for stream function formulation and results are presented using an isentropic flow assumption. Axial velocity profiles at rotor and stator blade edges are compared with published performance data of the NASA Task-1 stage transonic compressor and with numerical finite element results of Hirsch and Warzee.
dc.description.urihttp://archive.org/details/thefiniteelement1094517777
dc.language.isoen_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.
dc.subject.lcshAeronauticsen_US
dc.titleThe finite element method applied to flows in turbomachines.en_US
dc.typeThesisen_US
dc.contributor.secondreaderShreeve, Raymond P.
dc.contributor.corporateNaval Postgraduate School (U.S.)
dc.contributor.departmentAeronautics
dc.subject.authorfinite element methoden_US
dc.subject.authorturbomachinesen_US
dc.description.serviceLieutenant, United States Navy
etd.thesisdegree.nameM.S. in Aeronautical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAeronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
dc.description.distributionstatementApproved for public release; distribution is unlimited.


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