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dc.contributor.advisorHobson, Garth V.
dc.contributor.authorMartin, Michael J.
dc.dateJun-13
dc.date.accessioned2013-08-01T16:51:46Z
dc.date.available2013-08-01T16:51:46Z
dc.date.issued2013-06
dc.identifier.urihttp://hdl.handle.net/10945/34703
dc.descriptionApproved for public release; distribution is unlimiteden_US
dc.description.abstractThis study determined the optimum number of blades on a 4-inch diameter cross-flow fan rotor such that the rotor produced a thrust-to-weight ratio over one, which will make vertical take-off possible. The commercial computational fluid dynamics software ANSYS CFX, along with the commercial computer-aided design software SolidWorks, was used to model and perform a parametric study on the number of rotor blades. This parametric study focused on the thrust output, power requirement, and efficiency of each design in order to determine the optimum number of blades at 8,000 RPM. After the analytical study was complete, working models of three different rotors were fabricated and tested to validate the results found using ANSYS CFX. The experimental and analytical models were successfully compared at speeds ranging from 4,000 to 7,000 RPM.en_US
dc.publisherMonterey, California: 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. As such, it is in the public domain, and under the provisions of Title 17, United States Code, Section 105, may not be copyrighted.en_US
dc.titleDevelopment of a cross-flow fan rotor for vertical take-off and landing aircraften_US
dc.contributor.secondreaderGannon, Anthony J.
dc.contributor.departmentMechanical And Aerospace Engineering
dc.subject.authorVertical take-offen_US
dc.subject.authorvertical take-off and landing (VTOL)en_US
dc.subject.authorcross-flow fan (CFF)en_US
dc.description.recognitionOutstanding Thesisen_US
dc.description.serviceEnsign, United States Navyen_US
etd.thesisdegree.nameMaster of Scienceen_US
etd.thesisdegree.nameMaster of Science in Mechanical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineMechanical Engineeringen_US


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