Flight Testing of DBD Plasma Separation Control System

Sidorenko, A. A.; Budovsky, A. D.; Pushkarev, A. N.; Маслов, А. А.

doi:10.2514/6.2008-373

Cited by 24 publications

(12 citation statements)

References 4 publications

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“…One attempt was made recently to mount a DBD actuator on the leading edge of the wing of a Jantar Standard SZD-48-3 sailplane. 127 It appears that the DBD system was able to affect the separation and lift characteristics of the wing surface, but the data were not particularly reliable and refined tests are needed.…”

Section: Flow Control By Dielectric Barrier Dischargementioning

confidence: 99%

A Critical Review of Electric and Electromagnetic Flow Control Research Applied to Aerodynamics

Braun

Lu²,

Wilson³

2008

39th Plasmadynamics and Lasers Conference

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Fifty years ago, publications began to discuss the possibilities of electromagnetic flow control (EMFC) to improve aerodynamic performance. This led to an era of research that focused on coupling the fundamentals of magnetohydrodynamics (MHD) with propulsion, control, and power generation systems. Unfortunately, very few designs made it past an experimental phase as, among other issues, power consumption was unreasonably high. Recent proposed advancements in technology like the MARIAH hypersonic wind tunnel and the AJAX scramjet engine have led to a new phase of MHD research in the aerospace industry, with many interdisciplinary applications. Aside from propulsion systems and channel flow accelerators, electromagnetic flow control concepts applied to control surface aerodynamics have not seen the same level of advancement that may eventually produce a device that can be integrated with an aircraft or missile. Therefore, the purpose of this paper is to review the overall feasibility of the different electric and electromagnetic flow control concepts. Emphasis is placed on EMFC and experimental work.

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Section: Flow Control By Dielectric Barrier Dischargementioning

confidence: 99%

A Critical Review of Electric and Electromagnetic Flow Control Research Applied to Aerodynamics

Braun

Lu²,

Wilson³

2008

39th Plasmadynamics and Lasers Conference

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“…Published studies on relatively large-scale configurations have included a study 15 of DBD-based flight control of the USAF/Boeing 1303 UCAV configuration at a chord Reynolds number of 4 × 10 5 , and flight testing on a sailplane. 16 The present program differs from these previous studies in that the hot-film sensors provide a direct indication of flow separation (unlike pressure measurements), and that the system has been demonstrated on a relatively large-scale configuration suitable for SensorCraft 2 applications. The program had two main objectives:…”

Section: Introductionmentioning

confidence: 98%

Closed-Loop Stall Control on a Morphing Airfoil Using Hot-Film Sensors and DBD Actuators

Poggie

Tilmann

Flick

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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A closed-loop, stall sense and control system was demonstrated on a morphing airfoil. The FlexSys, Inc. Mission Adaptive Compliant Wing (MACW) was modified to accept a Boeing Co. dielectric barrier discharge (DBD) actuator panel in a location immediately upstream of the trailing-edge morphing flap, and hot-film sensors were installed on the model surface. A signal analysis algorithm, developed by Tao Systems, Inc, was applied to the hot-film signals to detect separation and trigger activation of the DBD actuators. The system was successfully demonstrated in the AFRL SARL wind tunnel facility, and an improvement in lift of about 10% was observed at Mach 0.05 (chord Reynolds number 9 × 10 5 ) under closed-loop control and a turbulent boundary layer state. Actuator effectiveness was demonstrated up to Mach 0.1, but must be extended to Mach 0.2-0.3 to enable a practical stall control system for takeoff and approach of large aircraft. * Cleared for public release, distribution unlimited (88ABW-2009-4976).

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“…A great number of experimen tal works have been performed to date (see, e.g., reviews [5,6]), where the feasibility of this control method was demonstrated. Relevant flight and wind tunnel experiments have been carried out in the Insti tute of Theoretical and Applied Mechanics (Siberian Branch, Russian Academy of Sciences) in recent years [7,8]. In the latter ones, the efficiency of the DBD for controlling the flow separation from straight and swept wings [9], as well as for controlling the vortex burst on the downwind side of the delta wing [10], has been proved.…”

Section: Introductionmentioning

confidence: 99%

Investigation of a nonstationary flow field generated by a dielectric barrier discharge

et al. 2012

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The search for ways of controlling a flow over flight vehicles is today an extremely topical issue, since the limiting capabilities of standard control methods are the bulk of the progress of space technology. A promising technique in this respect is the application of activators using a low temperature plasma. Specifi cally, these electrogasdynamic devices can directly convert electrical energy to a mechanical action on the flow. An activator based on a dielectric barrier discharge is considered. The nonstationary behavior of the acti vator is studied by measuring the electrodynamic parameters of the discharge and also by measuring induced velocity fields with particle image velocimetry. The instantaneous and integral parameters of the gas acceler ation stage are found, and the efficiency of the activator is determined.

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Flight Testing of DBD Plasma Separation Control System

Cited by 24 publications

References 4 publications

A Critical Review of Electric and Electromagnetic Flow Control Research Applied to Aerodynamics

A Critical Review of Electric and Electromagnetic Flow Control Research Applied to Aerodynamics

Closed-Loop Stall Control on a Morphing Airfoil Using Hot-Film Sensors and DBD Actuators

Investigation of a nonstationary flow field generated by a dielectric barrier discharge

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