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dc.creatorMoeller, Edward Brian
dc.date.accessioned2012-06-07T22:56:48Z
dc.date.available2012-06-07T22:56:48Z
dc.date.created1999
dc.date.issued1999
dc.identifier.urihttp://hdl.handle.net/1969.1/ETD-TAMU-1999-THESIS-M63
dc.descriptionDue to the character of the original source materials and the nature of batch digitization, quality control issues may be present in this document. Please report any quality issues you encounter to digital@library.tamu.edu, referencing the URI of the item.en
dc.descriptionIncludes bibliographical references (leaves 99-104).en
dc.descriptionIssued also on microfiche from Lange Micrographics.en
dc.description.abstractAn experimental investigation of hingeless flow control by vortex breakdown manipulation over a delta wing is described. Employed as a method of longitudinal control for slender wing platforms, the performance of this active flow control technique was evaluated as a possible replacement to conventional moving or hinged control surfaces. Testing was conducted with a 60-degree delta wing model incorporating Pneumatic Vortex Control (PVC) actuators. These actuators delivered high pressure jets of varying parameters upon the upper surface of the model. The jets were used to alter the flowfield over the wing caused by leading edge vortices. The natural location of vortex breakdown was shifted by three sets of PVC actuators strategically positioned on the model. This effect was intended to control the chord-wise lift distribution over the wing by inducing both premature and delayed vortex breakdowns to result in nose-up and nose-down pitch responses, respectively. A low speed comparative analysis of this hingeless flow control concept was conducted in Texas A&M University's 3' x 4' low speed wind tunnel and 2' x 3'water tunnel. Testing included force balance measurements, underwater laser/fluorescence visualizations, surface flow visualizations, and Schlieren shadowgraph visualizations. Visualization results show successful manipulation of the vortex breakdown locations over the delta wing model. Force balance results also show that the aerodynamic characteristics of the delta wing were altered. Observations show changes primarily in pitching moment, with no detrimental changes in lift or drag.en
dc.format.mediumelectronicen
dc.format.mimetypeapplication/pdf
dc.language.isoen_US
dc.publisherTexas A&M University
dc.rightsThis thesis was part of a retrospective digitization project authorized by the Texas A&M University Libraries in 2008. Copyright remains vested with the author(s). It is the user's responsibility to secure permission from the copyright holder(s) for re-use of the work beyond the provision of Fair Use.en
dc.subjectaerospace engineering.en
dc.subjectMajor aerospace engineering.en
dc.titleHingeless flow control over delta wing planformsen
dc.typeThesisen
thesis.degree.disciplineaerospace engineeringen
thesis.degree.nameM.S.en
thesis.degree.levelMastersen
dc.type.genrethesisen
dc.type.materialtexten
dc.format.digitalOriginreformatted digitalen


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