End plate gap effects on a half-wing model

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dc.contributor.authorKuppa, Subrahmanyamen
dc.contributor.committeechairMarchman, James F. IIIen
dc.contributor.committeememberSchetz, Joseph A.en
dc.contributor.committeememberNeu, Wayne L.en
dc.contributor.departmentAerospace Engineeringen
dc.date.accessioned2014-03-14T21:41:53Zen
dc.date.adate2012-08-01en
dc.date.available2014-03-14T21:41:53Zen
dc.date.issued1987-04-15en
dc.date.rdate2012-08-01en
dc.date.sdate2012-08-01en
dc.description.abstractDifferences in the aerodynamic performance data obtained at different test facilities were observed for the Wortmann FX-63-l37 airfoil. Earlier investigations found that the size of the hysteresis loop was affected by the tunnel environment and that single strut mounting of a three dimensional wing model interfered negligibly with the wing. Theoretical and experimental evaluations of a half wing model mounted with an end plate gap were done. Vortex panel method was used in the theoretical evaluation. The results from this indicated an effect of reduced aspect ratio with increase in end plate gap size. Tests were conducted in the VPI Stability Tunnel at low Reynolds numbers for different gap sizes including sealed gap. Results from the experiments showed that even very small gaps produce substantial changes in zero lift angle of attack (αu) and the change in αu, was reduced as Reynolds number increased. Sealed gap test results did not show such a behavior. Flow visualization of the flow through the gap showed a significant flow through the gap even at very low Reynolds number and small gap size.en
dc.description.degreeMaster of Scienceen
dc.format.extentx, 103 leavesen
dc.format.mediumBTDen
dc.format.mimetypeapplication/pdfen
dc.identifier.otheretd-08012012-040147en
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-08012012-040147/en
dc.identifier.urihttp://hdl.handle.net/10919/44054en
dc.publisherVirginia Techen
dc.relation.haspartLD5655.V855_1987.K78.pdfen
dc.relation.isformatofOCLC# 16655798en
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subject.lccLD5655.V855 1987.K78en
dc.subject.lcshDrone aircraften
dc.subject.lcshReynolds numberen
dc.subject.lcshVehicles, Remotely piloteden
dc.titleEnd plate gap effects on a half-wing modelen
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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