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dc.contributor.advisorEarll M. Murman.en_US
dc.contributor.authorDenis, Amandine, 1981-en_US
dc.contributor.otherMassachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.en_US
dc.date.accessioned2005-09-27T18:56:36Z
dc.date.available2005-09-27T18:56:36Z
dc.date.copyright2004en_US
dc.date.issued2004en_US
dc.identifier.urihttp://hdl.handle.net/1721.1/28898
dc.descriptionThesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2004.en_US
dc.descriptionIncludes bibliographical references (p. 105-108).en_US
dc.description.abstractThis thesis studies the influence of the roll-up of a wake on the benefits in induced drag and rolling moment experienced by a close formation of two elliptically loaded wings. The roll-up of the leading wake is computed in the Trefftz plane using a linear vorticity panel method. A smoothing parameter as well as a truncation of the vortex sheet in the highly rolled-up areas are introduced in order to stabilize the computations. The trailing wing is simply modeled as a lifting line, and its induced drag is computed thanks to a near-field analysis. The results are compared to computations using simple horseshoe-vortex methods, either with or without a viscous core. Maximum induced drag benefits comprised between 60% and 70% are observed for a lateral overlap of both wings of about 5% to 10% of the span. The maximum rolling moment is in average attained for 1.5% of the span less overlap. It is found that a horseshoe vortex with a viscous core of radius over semi-span ratio (2r[c])/b = 0.12 modeled according to Burnham can account well for the effects of the roll-up of the wake on the benefits in induced drag that can be gained from formation flight. Actually, the difference between both results is mainly confined in a small region around the maximum and the relative error is generally low. Taking the vertical drift of the whole wake into account is not found to be beneficial to the agreement between the results around the maximum. In the case of the rolling moment, the predictions given by simple horseshoe vortex models do not agree very well with the predictions given by the rolled-up sheet model, the relative error between both predictions being very high in many areas.en_US
dc.description.statementofresponsibilityby Amandine Denis.en_US
dc.format.extent199 p.en_US
dc.format.extent6956972 bytes
dc.format.extent6980599 bytes
dc.format.mimetypeapplication/pdf
dc.format.mimetypeapplication/pdf
dc.language.isoen_US
dc.publisherMassachusetts Institute of Technologyen_US
dc.rightsM.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission.en_US
dc.rights.urihttp://dspace.mit.edu/handle/1721.1/7582
dc.subjectAeronautics and Astronautics.en_US
dc.titleA simplified vortex sheet roll-up method for formation flighten_US
dc.typeThesisen_US
dc.description.degreeS.M.en_US
dc.contributor.departmentMassachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.en_US
dc.contributor.departmentMassachusetts Institute of Technology. Department of Aeronautics and Astronautics
dc.identifier.oclc60458708en_US


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