Control of Boundary Layer Separation and the Wake of an Airfoil using ns-DBD Plasma Actuators

Persistent Link:
http://hdl.handle.net/10150/605119
Title:
Control of Boundary Layer Separation and the Wake of an Airfoil using ns-DBD Plasma Actuators
Author:
Ashcraft, Timothy Allen
Issue Date:
2016
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:
The efficacy of nanosecond pulse driven dielectric barrier discharge (ns-DBD) plasma actuators for boundary layer separation and wake control is investigated experimentally. A single ns-DBD plasma actuator is placed at the leading edge of a NACA 0012 airfoil model. Both baseline and controlled flow fields are studied using static pressure measurements, Particle Image Velocimetry (PIV) and Constant Temperature Anemometry (CTA). Experiments are primarily performed at Re = 0.74 x 10⁶ and α = 18°. CP, PIV and CTA data show that a forcing frequency of F⁺ = 1.14 is optimal for separation control. CTA surveys of the wake at x/c = 7 indicate three approximate regimes of behavior. Forcing in the range 0.92 < F⁺ < 1.52 results in the best conditions for separation control over the airfoil, but has no dominant signature in the wake at x/c = 7. Excitation in the range of 0.23 < F⁺ < 0.92 produces a single dominant frequency in the wake while F⁺ < 0.23 shows behavior representing a possible impulse response or nonlinear effects. PIV data confirm these observations in all three regimes. Cross-correlations of CTA data are also employed to evaluate the two-dimensionality of the excited wake. The initial results presented here are part of an ongoing effort to use active flow control (AFC), in the form of ns-DBDs, as an enabling technology for the study of unsteady aerodynamics and vortex-body interactions.
Type:
text; Electronic Thesis
Keywords:
Aerospace Engineering
Degree Name:
M.S.
Degree Level:
masters
Degree Program:
Graduate College; Aerospace Engineering
Degree Grantor:
University of Arizona
Advisor:
Little, Jesse

Full metadata record

DC FieldValue Language
dc.language.isoen_USen
dc.titleControl of Boundary Layer Separation and the Wake of an Airfoil using ns-DBD Plasma Actuatorsen_US
dc.creatorAshcraft, Timothy Allenen
dc.contributor.authorAshcraft, Timothy Allenen
dc.date.issued2016en
dc.publisherThe University of Arizona.en
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
dc.description.abstractThe efficacy of nanosecond pulse driven dielectric barrier discharge (ns-DBD) plasma actuators for boundary layer separation and wake control is investigated experimentally. A single ns-DBD plasma actuator is placed at the leading edge of a NACA 0012 airfoil model. Both baseline and controlled flow fields are studied using static pressure measurements, Particle Image Velocimetry (PIV) and Constant Temperature Anemometry (CTA). Experiments are primarily performed at Re = 0.74 x 10⁶ and α = 18°. CP, PIV and CTA data show that a forcing frequency of F⁺ = 1.14 is optimal for separation control. CTA surveys of the wake at x/c = 7 indicate three approximate regimes of behavior. Forcing in the range 0.92 < F⁺ < 1.52 results in the best conditions for separation control over the airfoil, but has no dominant signature in the wake at x/c = 7. Excitation in the range of 0.23 < F⁺ < 0.92 produces a single dominant frequency in the wake while F⁺ < 0.23 shows behavior representing a possible impulse response or nonlinear effects. PIV data confirm these observations in all three regimes. Cross-correlations of CTA data are also employed to evaluate the two-dimensionality of the excited wake. The initial results presented here are part of an ongoing effort to use active flow control (AFC), in the form of ns-DBDs, as an enabling technology for the study of unsteady aerodynamics and vortex-body interactions.en
dc.typetexten
dc.typeElectronic Thesisen
dc.subjectAerospace Engineeringen
thesis.degree.nameM.S.en
thesis.degree.levelmastersen
thesis.degree.disciplineGraduate Collegeen
thesis.degree.disciplineAerospace Engineeringen
thesis.degree.grantorUniversity of Arizonaen
dc.contributor.advisorLittle, Jesseen
dc.contributor.committeememberLittle, Jesseen
dc.contributor.committeememberChan, Choliken
dc.contributor.committeememberKerschen, Edwarden
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