Nanosecond Pulse Dielectric Barrier Discharge Plasma Actuation in Supersonic Flow

Persistent Link:
http://hdl.handle.net/10150/243933
Title:
Nanosecond Pulse Dielectric Barrier Discharge Plasma Actuation in Supersonic Flow
Author:
Davis, Amanda Kathryn
Issue Date:
May-2012
Publisher:
The University of Arizona.
Rights:
Copyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction or presentation (such as public display or performance) of protected items is prohibited except with permission of the author.
Abstract:
Boundary layer control is a topic of constant concern in the area of aerodynamics. This study addresses a possible new method of affecting boundary layers and shock structure in supersonic flow. Nanosecond pulse dielectric barrier discharge plasma actuators are tested on a flat plate in a supersonic wind tunnel. Effects were observed using schlieren imaging to analyze changes in density gradients in the flow. While no noticeable results were found, the flow Mach numbers and electrical characteristics tested were very limited in variety due to complications with discharge formation and plate design. Much was learned to suggest improvements for further testing and this will facilitate later tests of similar technologies in this area of interest.
Type:
text; Electronic Thesis
Degree Name:
B.S.E.
Degree Level:
bachelors
Degree Program:
Honors College; Engineering Physics
Degree Grantor:
University of Arizona

Full metadata record

DC FieldValue Language
dc.language.isoenen_US
dc.titleNanosecond Pulse Dielectric Barrier Discharge Plasma Actuation in Supersonic Flowen_US
dc.creatorDavis, Amanda Kathrynen_US
dc.contributor.authorDavis, Amanda Kathrynen_US
dc.date.issued2012-05-
dc.publisherThe University of Arizona.en_US
dc.rightsCopyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction or presentation (such as public display or performance) of protected items is prohibited except with permission of the author.en_US
dc.description.abstractBoundary layer control is a topic of constant concern in the area of aerodynamics. This study addresses a possible new method of affecting boundary layers and shock structure in supersonic flow. Nanosecond pulse dielectric barrier discharge plasma actuators are tested on a flat plate in a supersonic wind tunnel. Effects were observed using schlieren imaging to analyze changes in density gradients in the flow. While no noticeable results were found, the flow Mach numbers and electrical characteristics tested were very limited in variety due to complications with discharge formation and plate design. Much was learned to suggest improvements for further testing and this will facilitate later tests of similar technologies in this area of interest.en_US
dc.typetexten_US
dc.typeElectronic Thesisen_US
thesis.degree.nameB.S.E.en_US
thesis.degree.levelbachelorsen_US
thesis.degree.disciplineHonors Collegeen_US
thesis.degree.disciplineEngineering Physicsen_US
thesis.degree.grantorUniversity of Arizonaen_US
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