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A numerical study of the effects of leading edge vortex flaps on the performance of a 75° delta wing

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dc.contributor.authorMcNutt, Mary Ellenen
dc.contributor.departmentAerospace Engineeringen
dc.date.accessioned2019-01-31T18:27:25Zen
dc.date.available2019-01-31T18:27:25Zen
dc.date.issued1982en
dc.description.abstractUsing a general, unsteady, nonlinear vortex lattice method, the aerodynamic loads have been found on a 75° delta wing with and without leading edge vortex flaps. The flap had an area approximately 26 percent of the wing area with a constant chord of 6.7 percent of the wing mean aerodynamic chord and was deflected at 30°. Results for lift, drag, axial force, and pitching moment coefficients are compared with experimental data and show very good agreement. Individual pressure difference coefficients along the wing and flap are also presented and compared with experimental data. Overall, the method shows the leading edge vortex flap to be very effective in reducing drag while maintaining lift comparable to that of the plain wing.en
dc.description.degreeMaster of Scienceen
dc.format.extentv, 48, [1] leavesen
dc.format.mimetypeapplication/pdfen
dc.identifier.urihttp://hdl.handle.net/10919/87232en
dc.language.isoen_USen
dc.publisherVirginia Polytechnic Institute and State Universityen
dc.relation.isformatofOCLC# 8433593en
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subject.lccLD5655.V855 1982.M336en
dc.subject.lcshLeading edges (Aerodynamics)en
dc.subject.lcshAirplanes -- Wings, Triangularen
dc.subject.lcshFlaps (Airplanes)en
dc.subject.lcshVortex-motionen
dc.titleA numerical study of the effects of leading edge vortex flaps on the performance of a 75° delta wingen
dc.typeThesisen
dc.type.dcmitypeTexten
thesis.degree.disciplineAerospace Engineeringen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.levelmastersen
thesis.degree.nameMaster of Scienceen

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