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dc.contributor.advisorPlatzer, Max F.
dc.contributor.authorCarrier, Alain
dc.dateDecember 1995
dc.date.accessioned2013-04-29T22:49:09Z
dc.date.available2013-04-29T22:49:09Z
dc.date.issued1995-12
dc.identifier.urihttp://hdl.handle.net/10945/31285
dc.description.abstractThe objective of this thesis was to contribute to the development of a second-order approximation to the steady and oscillatory lifting flow past low aspect ratio wings by establishing the validity of a NASA-Ames developed incompressible three-dimensional flow panel code named PMARC, which would subsequently be used to test the range of validity of this second-order theory. The steady state configurations modelled in the validation process include swept back, delta and rectangular wings, an F5 wing and three equivalent bodies of revolution. Oscillatory cases were also run with one delta and the F5 wings and their respective equivalent bodies of revolution, as well as with one spindle. In steady state, comparison with experimental and theoretical data proved PMARC to be very accurate for lift and pressure calculations, but revealed a discrepancy in the velocity distribution calculation around delta wings. This finding was corroborated by applying the slender body/slender wing theory (Oswatitsch-Keune theory) to the delta wing. The unsteady state results are presented, but their validation is left for future work. As part of its primary objective, this thesis also presents a computer code that generates the F5 wing equivalent body of revolution from its chordwise section definition. In order to be used as base software to the second-order theory, PMARC will have to be corrected, or a new software will have to be validated.en_US
dc.description.urihttp://archive.org/details/computationalinv1094531285
dc.format.extent248 p.en_US
dc.language.isoen_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.titleComputational investigation of low speed flow over low aspect ratio aircraft configurationsen_US
dc.typeThesisen_US
dc.contributor.departmentAeronautical Engineering
dc.description.funderNAen_US
dc.description.recognitionNAen_US
dc.description.serviceCanadian Armed Forces author.en_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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