Effects of Duty Cycles of the Plasma Actuators on Improvement of Pressure Distribution Above a NLF0414 Airfoil

Taleghani, Arash Shams; Shadaram, Abdollah; Mirzaei, Mehran

doi:10.1109/tps.2012.2187683

Cited by 26 publications

(18 citation statements)

References 12 publications

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“…They reported suppression of flow separation at speeds of up to 30 m/s along with decreased vortex shedding from the airfoil flap, consistent with the findings of Kotsonis et al (2014). In another study, Taleghani et al (2012) installed three plasma actuators on an NLF0414 airfoil and were able to improve the lift of the airfoil by up to 17% at optimum setup of duty cycle and excitation frequency. Further, in a similar study on a NACA0012 airfoil with a Gurney flap, Feng et al (2012) showed that using a DBD actuator a reasonable gain in lift is achieved with a minor drag penalty for their particular setup.…”

Section: Introductionsupporting

confidence: 67%

Experimental Investigation of Separation Control on a NACA0024 Airfoil using Stationary and Non-Stationary AC-Dielectric Barrier Discharge Plasma Actuator

Tathiri

Parishani²,

Pouryoussefi³

et al. 2016

JAFM

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An experimental study of stationary and non-stationary dielectric barrier discharge (DBD) plasma actuator is presented to control the flow around a NACA0024 airfoil. First, an induced air velocity of ~5 m/s is generated on a flat plate in still air using an AC-DBD actuator to find the optimal setup of the actuator (voltage, frequency, electrode width and gap size). Using the same actuator in the optimal position/setup on a NACA0024 airfoil at Reynolds number of 0.48×10 6 , we are able to increase the stall angle of the airfoil to 18º, compared to 16º in no-actuator state. Furthermore, during the plasma actuation, the lift is increased by up to 5%. We show that non-stationary actuation, while yielding a performance similar to stationary actuation, leads to a considerable reduction of ~51% in plasma power consumption.

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Section: Introductionsupporting

confidence: 67%

Experimental Investigation of Separation Control on a NACA0024 Airfoil using Stationary and Non-Stationary AC-Dielectric Barrier Discharge Plasma Actuator

Tathiri

Parishani²,

Pouryoussefi³

et al. 2016

JAFM

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“…In particular, due to the capacitive nature of the DBD, the rising and falling edges of high slew-rate pulses generate very short-high intensity current spikes, which are found to promote the plasma homogeneity [18], [19].…”

Section: A Short Bipolar Voltage Pulsesmentioning

confidence: 99%

Efficiency of an Exciplex DBD Lamp Excited Under Different Methods

Florez¹,

Schitz²,

Piquet³

et al. 2018

IEEE Trans. Plasma Sci.

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OATAO is an open access repository that collects the work of Toulouse researchers and makes it freely available over the web where possible. Abstract-Three different electrical generators have been designed and used to supply an exciplex dielectric barrier discharge lamp in order to elucidate the influence of each one of these supplying strategies over the system performance; the first method consists on supplying the lamp with short bipolar voltage pulses; the second and third methods are based on semiresonant converters were current pulses, of controlled duration and magnitude, are injected into the lamp. For each one of the generators, measurements of the lamp and supply efficiency, are performed and analyzed, at different levels of power (up to 130 W) and operating frequencies (60-90 kHz). From the experimental results, the pulsed voltage-mode approach has allowed obtaining the highest lamp efficiency (7%), yet the maximum supply efficiency is offered by the resonant mode supplies. On the basis of the lamp and the supply efficiencies, the whole system performance is analyzed.Index Terms-Dielectric-barrier discharge (DBD), exciplex lamp, pulsed voltage, resonant converter, ultraviolet.

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“…They reported that input energy influences the plasma actuator effectiveness in flow control around the turbine blade. [23] Zheng et al [21] reported that increase in actuation frequency is suppressed the flow separation and delayed it downstream. In a numerical study of Khoshkoo and Jahangirian, [19] the effect of the unsteady plasma body force is compared with that of steady force over a stalled NACA0015 airfoil at Re = 4.5 × 10 4 .…”

Section: Introductionmentioning

confidence: 99%

“…However, it has also been reported that the effect of plasma with various duty cycles has no effect on pressure distribution at 16 • angle of attack and 100 Hz excitation frequency. [23] Zheng et al [21] reported that increase in actuation frequency is suppressed the flow separation and delayed it downstream. They also showed that the pulsed plasma has significant effects on separated shear layer, while the plasma actuators were placed close to flow separation.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic and energy‐efficiency‐based assessment of plasma actuator's position on a NACA0015 airfoil

Akbıyık

Yavuz

Akansu

2019

Contributions to Plasma Physics

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In recent years, there has been an increase in the number of research papers on plasma and its use in active flow control applications. The main objective of this study is to assess the plasma actuator's position on a NACA0015 airfoil in terms of aerodynamic forces. In addition, optimization of the plasma actuator's position and its configuration are studied in order to identify the optimum configuration for improvement in lift coefficient. The experiments are conducted in an open-suction-type wind tunnel at Reynolds numbers of 48,000, 75,000, and 100,000. The plasma actuators are mounted on various positions (x/C) starting from the leading edge to trailing edge of the airfoil. The experimental results on aerodynamic force measurement are presented to illustrate the increasing lift effect of the generated plasma. It is also shown that the plasma actuators used as an active flow control device appears to shift the stall angle of the airfoil. The results of the experimental study suggest that the energy efficiency of airborne systems can be improved with the use of plasma actuators due to its increasing lift coefficient effect. This result becomes a vital finding considering that the same flight can be achieved with less fuel and less amount of environmental pollution for the same distance of journey. It is also worth mentioning that increasing lift effect would mean taking off from a shorter runway or allowing the airborne vehicle with the ability to fly with additional payload. K E Y W O R D Sairfoil, energy efficiency, lift coefficient, plasma actuator, stall angle

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Effects of Duty Cycles of the Plasma Actuators on Improvement of Pressure Distribution Above a NLF0414 Airfoil

Cited by 26 publications

References 12 publications

Experimental Investigation of Separation Control on a NACA0024 Airfoil using Stationary and Non-Stationary AC-Dielectric Barrier Discharge Plasma Actuator

Experimental Investigation of Separation Control on a NACA0024 Airfoil using Stationary and Non-Stationary AC-Dielectric Barrier Discharge Plasma Actuator

Efficiency of an Exciplex DBD Lamp Excited Under Different Methods

Aerodynamic and energy‐efficiency‐based assessment of plasma actuator's position on a NACA0015 airfoil

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