Plasma Actuator Application on a Full-Scale Aircraft Tail

Keisar, David; Hasin, David; Greenblatt, David

doi:10.2514/1.j057233

Cited by 31 publications

(11 citation statements)

References 46 publications

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“…Still, despite their lower electromechanical efficiencies, than corona driven flow, DBD actuators are more effective at providing a consistent electro-hydrodynamic (EHD) force [4,9]. The current DBD applications are primarily limited to flow control at low-speed conditions due to their relatively lower EHD forces [14,18,19]. There are several fundamental aspects of DBD that are not well-understood such as the kinetics of ion recombination, ionization of different species, and coupling between discharge and fluid flow.…”

Section: Introductionmentioning

confidence: 99%

Empirical relations for discharge current and momentum injection in dielectric barrier discharge plasma actuators

Tang¹,

Vaddi²,

Mamishev³

et al. 2021

J. Phys. D: Appl. Phys.

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Dielectric barrier discharge (DBD) plasma actuators with an asymmetric, straight edge electrode configuration generate a wall-bounded jet without moving parts. Mechanistic description of the interaction between the Coulombic forces and fluid motion as a function of DBD parameters remains unclear. This paper presents an experimental investigation of DBD actuators, including electrical current associated with microdischarges, plasma volume and the wall jet momentum over a range of alternating current (AC) frequencies (0.5–2 kHz) and peak-to-peak voltages up to 19.5 kV. Discharge current is measured with a high temporal resolution, plasma volume is characterized optically and the momentum induced by the DBD wall jet is computed based on the axial velocities measured downstream of the actuator using a custom-built pitot tube. Discharge current analysis demonstrated asymmetry between the positive and negative semi-cycle; both currents yielded a power–law relationship with empirical fitting coefficients. Plasma length varies linearly and volume quadratically with voltage. Although plasma length reached an asymptotic value at a higher frequency, the plasma volume grows due to the increasing height of the ionization region. In a simple two-dimensional configuration, the DBD wall jet momentum shows near-linear dependency with discharge current in the range of voltages and frequencies considered in this work. The presented empirical model characterizes the DBD wall jet momentum and the discharge current based only on the AC inputs. With the estimation of plasma volume, the model can be applied for determining more realistic boundary conditions in numerical simulations.

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Section: Introductionmentioning

confidence: 99%

Empirical relations for discharge current and momentum injection in dielectric barrier discharge plasma actuators

Tang¹,

Vaddi²,

Mamishev³

et al. 2021

J. Phys. D: Appl. Phys.

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“…High AC voltage (10 kVpp) was supplied to the actuator by a Minipuls 2® highvoltage generator (GBS Elektronik GmbH) which, in turn, was supplied by CPX400D-Dual 420-watt DC power supply. The gross DC power input to the actuators (Pin) was monitored, and a desktop calibration on an identical flat actuator was carried out according to the method described in [50]. The maximum actuator axial body force (thrust) attained was 0.180 grams/meter.…”

Section: Methodsmentioning

confidence: 99%

“…DBD plasma actuators could therefore be pulsed modulated over a large frequency bandwidth limited only by fion. These frequencies were dictated by the Minipuls highvoltage generator, which responds like a non-linear second-order system with one or more resonance frequencies (see Table 1) [50]. This allowed us to adopt two different flow control strategies.…”

Section: Main Experimental Parametersmentioning

confidence: 99%

“…However, varying the duty cycle between 5% and 15% produced negligible differences in the results, even when a non-integer number of cycles was employed in the modulation bursts. Unlike previous research [50], no attempt was made to determine the minimum power required to attain a particular objective. ) are shown in Figure 2.…”

Section: Main Experimental Parametersmentioning

confidence: 99%

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Plasma-Based Dynamic Stall Control and Modeling on an Aspect-Ratio-One Wing

et al. 2022

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“…It may significantly improve post-stall lift coefficient and control authority of V-tail UAVs during crosswind take-off and landing (Keisar et al , 2019). PAs produce measurable roll moments suggesting that they may replace or enhance movable flight control surfaces (Vorobiev et al , 2008; Boesch et al , 2010).…”

Section: Introductionmentioning

confidence: 99%

Plasma actuation effect on a NACA 4412 airfoil

Karadag

Kolbakir²,

Durna³

2021

AEAT

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Purpose This paper aims to investigate the effects of a dielectric barrier discharge (DBD) plasma actuator (PA) qualitatively on aerodynamic characteristics of a 3 D-printed NACA 4412 airfoil model. Design/methodology/approach Airflow visualization study was performed at a Reynolds number of 35,000 in a small-scale open-loop wind tunnel. The effect of plasma actuation on flow separation was compared for the DBD PA with four different electrode configurations at 10°, 20° and 30° angles of attack. Findings Plasma activation may delay the onset of flow separation up to 6° and decreases the boundary layer thickness. The effects of plasma diminish as the angle of attack increases. Streamwise electrode configuration, in which electric wind is produced in a direction perpendicular to the freestream, is more effective in the reattachment of the airflow compared to the spanwise electrode configuration, in which the electric wind and the free stream are in the same direction. Practical implications The Reynolds number is much smaller than that in cruise aircraft conditions; however, the results are promising for low-velocity subsonic airflows such as improving control capabilities of unmanned aerial vehicles. Originality/value Superior efficacy of spanwise-generated electric wind over streamwise-generated one is demonstrated at a very low Reynolds number. The results in the plasma aerodynamics literature can be reproduced using ultra-low-cost off-the-shelf components. This is important because high voltage power amplifiers that are frequently encountered in the literature may be prohibitively expensive especially for resource-limited university aerodynamics laboratories.

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Plasma Actuator Application on a Full-Scale Aircraft Tail

Cited by 31 publications

References 46 publications

Empirical relations for discharge current and momentum injection in dielectric barrier discharge plasma actuators

Empirical relations for discharge current and momentum injection in dielectric barrier discharge plasma actuators

Plasma-Based Dynamic Stall Control and Modeling on an Aspect-Ratio-One Wing

Plasma actuation effect on a NACA 4412 airfoil

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