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dc.contributor.advisorFlatau, Alison Ben_US
dc.contributor.authorHaack, Sarah Joen_US
dc.date.accessioned2007-09-28T15:04:01Z
dc.date.available2007-09-28T15:04:01Z
dc.date.issued2007-09-17en_US
dc.identifier.urihttp://hdl.handle.net/1903/7421
dc.description.abstractThis thesis shows the time-averaged effect of plasma and synthetic jet actuators on flow over bluff body shapes for delaying flow separation and, therefore, reducing pressure drag. The percentage of pressure drag reduction is used to evaluate the effectiveness of these two unique actuators for varied applied voltage, actuator position and flow velocity on a circular cylinder and 2D extrusion of a rotorcraft tail boom cross section. Two non-dimensional parameters were used to evaluate the effect of the actuators: coefficient of momentum (Cμ) and non-dimensional surface distance between the location of the actuator and the flow separation point (SD). Both actuation techniques beneficially affect the pressure distribution by decreasing the pressure near the location of the actuators and increasing the pressure in the separated flow region. Contour plots displaying the variation of the percentage of drag reduction as Cμ and SD vary illustrate optimal operating conditions based on these parameters.en_US
dc.format.extent9550959 bytes
dc.format.mimetypeapplication/pdf
dc.language.isoen_US
dc.titleFlow Control Using Plasma and Synthetic Jet Actuators on Bluff Bodiesen_US
dc.typeThesisen_US
dc.contributor.publisherDigital Repository at the University of Marylanden_US
dc.contributor.publisherUniversity of Maryland (College Park, Md.)en_US
dc.contributor.departmentAerospace Engineeringen_US
dc.subject.pqcontrolledEngineering, Aerospaceen_US
dc.subject.pquncontrolledactive flow controlen_US
dc.subject.pquncontrolledplasma actuatoren_US
dc.subject.pquncontrolledsynthetic jet actuatoren_US
dc.subject.pquncontrolledcircular cylinderen_US
dc.subject.pquncontrolledbluff bodyen_US


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