Separation Control from the Flap of a High-Lift Airfoil Using DBD Plasma Actuators

Little, Jesse; Nishihara, Munetake; Adamovich, Igor; Samimy, Mo

doi:10.2514/6.2009-145

Cited by 13 publications

(9 citation statements)

References 39 publications

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“…Since the dominant effect of the NS-DBD actuator is known to be the thermal effect (namely, Joule heating) [17,19,28], in the numerical simulation the effect of the discharge of the NS-DBD actuator is represented as instantaneous gas heating [33]. In this paper, the NS-DBD numerical simulation is based on phenomenological theory.…”

Section: Discharge Position and Parameter Setting Of The Plasma Actuatormentioning

confidence: 99%

“…They believe that the main NS-DBD mechanism is the generation of a T-S disturbance wave, and thus the flow control mechanism of the NS-DBD may include a large-scale vortex, flow transitions, or other factors. Little et al [19][20][21], from Ohio State University, used a plasma aerodynamic actuator to conduct a study on simplified flow control of the high lift device. The results show that the plasma actuator with millisecond pulses can effectively control the separation of the boundary layer of the trailing edge flap at a Reynolds number of 2.4 × 10 5 -7.5 × 10 5 .…”

Section: Introductionmentioning

confidence: 99%

“…Leonov et al [26] believe that NS-DBD will generate random local thermal disturbance near the wall in a relatively long-time scale (> 100 us) after discharge, and will form compression wave in a very short time (1-10 us). Sergey, Unfer, Roupassov, Correale, Little, Adamovich et al [14,19,20,27,28] suggest that shock wave, which is the dominant factor of flow control, is generated after NS-DBD discharge due to thermal effect. This paper focuses on the research of NS-DBD plasma actuator on the control of increasing lift and reducing drag of two-section airfoil.…”

Section: Introductionmentioning

confidence: 99%

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Effect of NS-DBD Actuator Parameters on the Aerodynamic Performance of a Flap Lifting Device

Chen¹,

Wei

Shi

2019

Applied Sciences

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The flap lift device is an important part of the conventional configuration of aircrafts and has an important impact on the aerodynamic performance. In this paper, a high-efficiency, simple, and energy-saving nanosecond dielectric barrier discharge (DBD) plasma actuator is placed in the vicinity of the flap lift device to improve the aerodynamic performance of the flap by controlling the flow field. The two-dimensional airfoil GAW-1 and its 29% flap were selected as the research objects, and the nanosecond (NS) DBD actuators were fixed at different locations near the deflection angle of the 10°flap. The excitation frequency, pulse width, and energy density parameters of the pulse discharge were adjusted, and then, the effects of parameter changes on aerodynamic characteristics of the airfoil were studied by numerical simulation. The simulation results show that adjusting the excitation frequency on the aerodynamic drag is weak and that the effect on the aerodynamic lift is obvious. The increase of the discharge pulse width will have a more significant effect on the flow field, i.e., a proper increase of the discharge pulse width can achieve better drag reduction, and increase lift after a stall at a high angle of attack. Although the increase of discharge energy density can strengthen the pulse perturbation effect on the flow field, it also contributes to some adverse effects and has no obvious optimization effect on the control efficiency of lift increase and drag reduction.

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Section: Discharge Position and Parameter Setting Of The Plasma Actuatormentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Effect of NS-DBD Actuator Parameters on the Aerodynamic Performance of a Flap Lifting Device

Chen¹,

Wei

Shi

2019

Applied Sciences

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“…20 They are currently the topic of intensive international research. [10][11][12][13][14] The wind tunnel model was modified to include a plasma actuator panel located upstream of the flap. This panel was designed to mount flush with the upper-surface mold line of the airfoil.…”

Section: Plasma Actuatorsmentioning

confidence: 99%

“…The existing studies have used surface pressure sensors to detect separation, and have employed either synthetic jet actuators 8 or DBD actuators for stall mitigation. 9 Similarly, DBD actuators are a topic of intensive international research, [10][11][12][13][14] but there has been a lack of attention to the application of DBD actuators to large-scale configurations. 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.…”

Section: Introductionmentioning

confidence: 99%

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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High-lift airfoil trailing edge separation control using a single dielectric barrier discharge plasma actuator

et al. 2009

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Separation Control from the Flap of a High-Lift Airfoil Using DBD Plasma Actuators

Cited by 13 publications

References 39 publications

Effect of NS-DBD Actuator Parameters on the Aerodynamic Performance of a Flap Lifting Device

Effect of NS-DBD Actuator Parameters on the Aerodynamic Performance of a Flap Lifting Device

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

High-lift airfoil trailing edge separation control using a single dielectric barrier discharge plasma actuator

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