Flow Separation Control over a Boeing Vertol VR-7 using NS-DBD Plasma Actuators

Esfahani, Ata; Singhal, Achal; Clifford, Christopher J.; Samimy, Mo

doi:10.2514/6.2016-0843

Cited by 9 publications

(17 citation statements)

References 28 publications

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“…[13,14,15,11]. The formation of small structures (such as those produced by high excitation Strouhal numbers) only results in partial reattachment [13,14,15,11]. This is also observed in the PIV data presented ( To an extent, this is also observed by the phase-locked PIV data in Closer examination of Figure 4.11, indicates that there is fairly monotonic relationship between the excitation Strouhal number and the lift peak.…”

Section: Firstly Thesupporting

confidence: 57%

“…This behavior smooths out, as the excitation Strouhal number increases. given that higher excitation Strouhal numbers result in the formation of more, smaller structures further upstream on the airfoil which quickly develop, disintegrate, and dissipate [13,14,15,11]. Again, this is well captured by PIV data, shown in Figure 4.24.…”

Section: Firstly Thementioning

confidence: 74%

“…NS-DBD plasma actuators have been shown to reattach flow in stalled airfoils in a variety of airfoils and flow velocities in a static configuration [12,13,14,15,11]. This work aims to extend the existing body of work on NS-DBD flow control to unsteady flows.…”

Section: Conclusion Andmentioning

confidence: 99%

“…Thus, while similar signature oscillations may exist for the high-Strouhal number cases, they would not be manifest in this data. [13,14,15,11]. The formation of small structures (such as those produced by high excitation Strouhal numbers) only results in partial reattachment [13,14,15,11].…”

Section: Firstly Thementioning

confidence: 99%

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Unsteady Flow Separation Control over a NACA 0015 using NS-DBD Plasma Actuators

Singhal

2017

55th AIAA Aerospace Sciences Meeting

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Flow field surrounding a moving body is often unsteady. This motion can be linear or rotary, but the latter will be the primary focus of this thesis. Unsteady flows are found in numerous applications, including sharp maneuvers of fixed wing aircraft, biomimetics, wind turbines, and most notably, rotorcraft. Unsteady flows cause unsteady loads on the immersed bodies. This can lead to aerodynamic flutter and mechanical failure in the body. Flow control is hypothesized to reduce the load hysteresis, and is achieved in the present work via nanosecond pulse driven dielectric barrier discharge (NS-DBD) plasma actuators. To better understand the physics of unsteady flow over an airfoil a new facility was constructed, and new processing codes were developed and implemented. A NACA 0015 airfoil was mounted to oscillating mechanism, and the angle of attack was varied sinusoidally. The Reynolds number was varied from 0.17 • 10 6 − 0.50 • 10 6 , and the reduced frequency of oscillation was varied from 0.025 − 0.075 to gain a better understanding of these parameters on the unsteady flow dynamics. The plasma actuator was mounted at / = 0.01, just downstream of the airfoil leading edge. It was noted that the construction of the actuator influenced baseline behavior. Validation of the facility was achieved via qualitative comparisons of the baseline results to the results in a similar experimental setup in literature. After validation, As a first year student who wanted to explore the frontiers of technology, Dr. Samimy gave me with the opportunity to learn so much about flow control. These facilities, along with the wonderful group of students provided an engaging environment that I am truly grateful for. I am also thankful to Dr. Datta Gaitonde and Dr. James Gregory for making the graduation process an exciting one! Many thanks go to Dr. Igor Adamovich and Dr. Munetake Nishihara of the Non-Equilibrium Thermodynamics Laboratory for their work on nanosecond pulse driven dielectric barrier discharge plasma actuators. Their expertise was only surpassed by their willingness to provide assistance when needed. I cannot thank the many students of the Gas Dynamics and Turbulence Laboratory enough. Their encouragement, patience, and willingness, made even the long nights on the tunnel fun ones! My first day at the laboratory, I was greeted by Cameron DuBois who taught me the basics of the laboratory, and guided my curiosity. Dr. Chris Clifford challenged me to continually improve the facility, and I am grateful for the skills I gained in doing so. Special thanks to Dr. Michael Crawley, who among many other things, made my time here an entertaining one and to Dr. Nathan Webb for his support. David Castañeda helped acquire and analyze some of the results presented herein, and his help is much appreciated! I would also like to thank

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Section: Firstly Thesupporting

confidence: 57%

Section: Firstly Thementioning

confidence: 74%

Section: Conclusion Andmentioning

confidence: 99%

Section: Firstly Thementioning

confidence: 99%

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Unsteady Flow Separation Control over a NACA 0015 using NS-DBD Plasma Actuators

Singhal

2017

55th AIAA Aerospace Sciences Meeting

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“…The use of ns-DBD plasma actuators for separation control has been well documented in recent years on various airfoils (Roupassov et al 2009, Rethmel et al 2011, Little et al 2012, Kelley 2014, Esfahani 2016. During these experiments, separation control at higher flow speeds was achieved (up to Mach 0.85 and Re > 10 6 ) and there was little optimization of the device for such situations.…”

Section: Separation Control With Dbd Plasma Actuatorsmentioning

confidence: 99%