On the possibility of laminar flow control on a swept wing by means of plasma actuators

Chernyshev, S. L.; Kuryachii, A. P.; Manuĭlovich, S. V.; Rusyanov, Dmitriy Anatolyevich; Скворцов, В. В.

doi:10.1051/eucass/201507169

Cited by 4 publications

(8 citation statements)

References 40 publications

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“…For all the investigated configurations of table 2, the generated thrust is comparatively less than what reported by Chernyshev et al (2013) and Dörr & Kloker (2015b) in their studies. However, in the current study, the AC-DBD plasma jets are used in a respective fashion to isolated roughness elements for DRE/UFD flow control.…”

Section: Performancecontrasting

confidence: 57%

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Conditioning of cross-flow instability modes using dielectric barrier discharge plasma actuators

2017

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In the current study, selective forcing of cross-flow instability modes evolving on a 45• swept wing at Re = 2.17 · 10 6 is achieved by means of spanwise-modulated plasma actuators, positioned near the leading edge. In the perspective of laminar flow control, the followed methodology holds on the discrete roughness elements/upstream flow deformation (DRE/UFD) approach, thoroughly investigated by e.g. Saric et al. (1998);Malik et al. (1999) and Wassermann & Kloker (2002). The possibility of using active devices for UFD provides several advantages over passive means, allowing for a wider range of operating Re numbers and pressure distributions. In the present work, customised alternating current dielectric barrier discharge plasma actuators have been designed, manufactured and characterised. The authority of the actuators in forcing monochromatic stationary cross-flow modes at different spanwise wavelengths is assessed by means of infrared thermography. Moreover, quantitative spatio-temporal measurements of the boundary layer velocity field are performed using time-resolved particle image velocimetry. The results reveal distinct steady and unsteady forcing contributions of the plasma actuator on the boundary layer. It is shown that the actuators introduce unsteady fluctuations in the boundary layer, amplifying at frequencies significantly lower than the actuation frequency. In line with the DRE/UFD strategy, forcing a sub-critical stationary mode, with a shorter wavelength compared to the naturally selected mode, results in less amplified primary vortices and related fluctuations, compared to the critical forcing case. The effect of the forcing on the flow stability is further inspected by combining the measured actuators body-force with the numerical solution of the laminar boundary layer and linear stability theory. The simplified methodology yields fast and computationally cheap estimates on the effect of steady forcing (magnitude and direction) on the boundary layer stability.

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Section: Performancecontrasting

confidence: 57%

“…Grundmann & Tropea (2008); Kotsonis et al (2013Kotsonis et al ( , 2015). In contrast, usage of these devices in three-dimensional flows, dominated by CFI, is still rather limited (see Chernyshev et al (2013); Schuele et al (2013); Dörr & Kloker (2015b, 2016Shahriari (2016)). …”

Section: Plasma Actuators For Cross-flow Instability Controlmentioning

confidence: 99%

Conditioning of cross-flow instability modes using dielectric barrier discharge plasma actuators

2017

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“…This is another numerical challenge because characteristic times and lengths of the discharge are several orders of magnitude smaller with respect those related to the fluid-dynamic domain. Several authors [26][27][28][29][30][31][32][33][34][35][36] followed this computational strategy obtaining interesting results in good agreement with experimental fluid-dynamic effects. In Figure 6a, integrated horizontal body force as a function of the applied voltage is shown [36].…”

Section: Dbd Aerodynamic Actuators: Basic Principlesmentioning

confidence: 99%

“…Time evolution of the EHD body force (a)[36], and spatial distribution of the average horizontal force (b)[33].…”

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confidence: 99%

Active Flow Control by Using Plasma Actuators

Neretti¹

2016

Recent Progress in Some Aircraft Technologies

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Active flow control has recently received an increasing attention since it allows to directly manipulate the flow-field around a surface only when it is effectively requested. Aerodynamic plasma actuators supplied by a dielectric barrier discharge (DBD) can be used for this purpose. Usually, sinusoidal voltages in the range 5-50 kV peak and frequencies between 1 and 100 kHz are utilized to ignite this plasma typology. The surface discharge produced by these devices is able to tangentially accelerate the flow field by means of the electrohydrodynamic (EHD) interaction. DBDs generate non-thermal plasmas characterized by low input energies and limited temperature increments. Plasma actuators can be easily designed by following the shape of the aerodynamic body and can be used over heat-sensitive surfaces. These aerodynamic devices have demonstrated to produce boundary layer modifications with induced speeds up to 10 m/s. Their use over airfoils, flaps, and blades have shown the possibility to delay the transition between laminar to turbulent regime, to prevent flow separation enhancing lift and reducing drag. Moreover, the adoption of these actuators over landing gears and trailing edges may induce a noise reduction effect. Dielectric materials, electrodes configuration, and supplying waveforms are most relevant parameters to be considered to enhance actuator performance. On a parallel plane, on/off actuation strategy is a key point in the use of these devices when utilized over aerodynamic surfaces impinged within an external flow.

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Section: Dbd Aerodynamic Actuators: Basic Principlesmentioning

confidence: 99%

Recent Progress in Some Aircraft Technologies

Agarwal¹

2016

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This book is a compilation of research articles and review articles describing the latest advances in some engine technologies, active flow control, and morphing technologies and in topics related to aeroacoustics and aircraft controllers. The book is divided into three sections. Section 1 is titled "Engine Technologies." It has two papers dealing with progress in experimental research in turbine aeroacoustics and lubricants for turbine engines. Section 2 is titled "Actuators and Controllers." It has five chapters dealing with a wide variety of topics. The topics include active flow control by using plasma actuators, flight actuators testing and qualifications, morphing technologies (adaptive ailerons), self-healing control design under actuator fault occurrence on single-rotor unmanned helicopter, and a hierarchical tracking controller for quadrotor. Section 3 is titled "Miscellaneous Topics." It has two chapters; one describes studies on effects induced by aircraft noise, and the other is on numerical study of support interferences on SOAR separation wind tunnel test. Thus, the book covers a wide variety of topics related to several aircraft and engine technologies in nine chapters in a single volume. It is hoped that it can serve as a useful source of reference to both researchers and students interested in learning about certain specific aircraft technologies.

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On the possibility of laminar flow control on a swept wing by means of plasma actuators

Cited by 4 publications

References 40 publications

Conditioning of cross-flow instability modes using dielectric barrier discharge plasma actuators

Conditioning of cross-flow instability modes using dielectric barrier discharge plasma actuators

Active Flow Control by Using Plasma Actuators

Recent Progress in Some Aircraft Technologies

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