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Aerospace
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Plasma Actuator
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Plasma Actuator

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: closed (31 December 2023) | Viewed by 6363

Special Issue Editor

Dr. Ivan A. Moralev

E-Mail Website
Guest Editor
Joint Institute for High Temperatures, Division of Magneto-Plasma Aerodynamics and MHD Energy Conversion, 125412 Moscow, Russia
Interests: aerodynamics; actuators; experimental fluid mechanics; particle image velocimetry; laser-induced fluorescence; dielectric barrier discharge; boundary layer flow; instability and transition to turbulence; flow acoustics; plasma diagnostics; plasma technology; magnetohydrodynamics

Special Issue Information

Dear Colleagues,

In the last three decades, plasma actuators have attracted wide attention in the aerodynamic community as a novel flow control technique. The studies covered a variety of hydrodynamic problems including supersonic flow control by heat release and MHD interaction, the control of boundary layer transition and turbulent friction, airframe and jet noise reduction, and many others. Presently, plasma actuators are used by many groups in the laboratory as a high-frequency, robust disturbance source in transition experiments.

New applications, such as reducing turbulent friction or reactive control in transition studies, set new challenges for the plasma actuators community, posed at the border of hydrodynamics, low-temperature plasmas, and material science. The new issues cover the problems of the electrodes’ durability, signal-to-noise ratio, and spatial resolution of the plasma-based flow control devices.

We invite you to apply your research to the Special Issue “Plasma Actuators”. The aim of this issue is to provide a reader with a perspective of plasma actuators’ physics and applications, focusing on new problems and challenges. 

Scope: The papers collected will cover the following topics:

  1. A variety of flow control problems, utilizing gas discharge devices as actuators: turbulent boundary layer control, transition delay in boundary layers and jets, wake control for bluff bodies, SWBLI interaction, etc.;
  2. Problems in gas discharge physics, related to the flow control applications, including, but not limited to electrodes and dielectric durability studies, noise generation, and actuator operation envelope;
  3. New approaches for low-temperature plasma applications in aerodynamic problems.

Dr. Ivan A. Moralev
Guest Editor

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • plasma actuator
  • flow control
  • flow instability and turbulence
  • gas discharge
  • low-temperature plasma
  • boundary layer
  • jets
  • shock wave-boundary layer interaction
  • airframe noise
  • jet noise
  • aerodynamic wake

Published Papers (5 papers)

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Research

11 pages, 3587 KiB  
Article
Closed-Loop Cavity Shear Layer Control Using Plasma Dielectric Barrier Discharge Actuators
by Pavel N. Kazanskii
Aerospace 2023, 10(10), 888; https://doi.org/10.3390/aerospace10100888 - 18 Oct 2023
Cited by 1 | Viewed by 1001
Abstract
The complex unsteady flow in cavities leads to the formation of large-scale disturbances in the shear layer. Natural closed-loop mechanisms provoke a dramatic increase in pressure pulsations and aerodynamic noise. This paper presents the experimental study of pressure fluctuations in closed-loop control in [...] Read more.
The complex unsteady flow in cavities leads to the formation of large-scale disturbances in the shear layer. Natural closed-loop mechanisms provoke a dramatic increase in pressure pulsations and aerodynamic noise. This paper presents the experimental study of pressure fluctuations in closed-loop control in rectangular cavities using plasma dielectric barrier discharge. The flow velocity was 37 m/s, and the Reynolds number based on a cavity depth was approximately 120,000. The discharge ignition near the leading edge of the cavity provoked the shear layer restructuring. It was found that pressure fluctuations with an amplitude of 120 dB occur at frequencies 480 and 820 Hz. Frequency modulation of the discharge at resonant peaks was carried out by changing the phase shift of the power supply. The peak amplitude was reduced or increased by phase shifts from natural disturbances to forced ones. The optimum energy input was 50 W/m. This was three times less than the power consumption of the open-loop mode. The PIV visualization was organized in the phase-locked mode. The pressure spectrum corresponds to the magnitude of coherent structures in the shear layer of the cavity. Full article
(This article belongs to the Special Issue Plasma Actuator)
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18 pages, 11090 KiB  
Article
3D Turbulent Boundary Layer Separation Control by Multi-Discharge Plasma Actuator
by Sergey Chernyshev, Gadzhi Gadzhimagomedov, Aleksandr Kuryachiy, Dmitry Sboev and Stepan Tolkachev
Aerospace 2023, 10(10), 869; https://doi.org/10.3390/aerospace10100869 - 06 Oct 2023
Cited by 1 | Viewed by 894
Abstract
In a subsonic wind tunnel, a three-dimensional separation of a developed turbulent boundary layer was simulated on a swept wing flap model. A multi-discharge plasma actuator operating on the basis of dielectric barrier discharge was used to overcome the positive pressure gradient, leading [...] Read more.
In a subsonic wind tunnel, a three-dimensional separation of a developed turbulent boundary layer was simulated on a swept wing flap model. A multi-discharge plasma actuator operating on the basis of dielectric barrier discharge was used to overcome the positive pressure gradient, leading to a three-dimensional separation, when the ultimate streamline on the aerodynamic surface turns along the flap trailing edge. The actuator created an extended streamwise region of volume force, leading to flow acceleration near a streamlined surface. The influence of the force impact direction relative to the flap trailing edge was studied. The experiments demonstrated that the plasma actuator can significantly influence the flow structure in the separation region, leading to a decrease in both the transverse size of the viscous wake behind the flap and the total pressure losses within it. Full article
(This article belongs to the Special Issue Plasma Actuator)
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24 pages, 9454 KiB  
Article
Response of the Shock Wave/Boundary Layer Interaction to Disturbances Induced by the Plasma Discharge
by Oleg Vishnyakov, Pavel Polivanov and Andrey Sidorenko
Aerospace 2023, 10(9), 798; https://doi.org/10.3390/aerospace10090798 - 13 Sep 2023
Cited by 1 | Viewed by 1165
Abstract
The paper focuses on the investigation of unsteady effects in shock wave/boundary layer interaction. The study was carried out using a flat plate model subjected to a free stream Mach number of 1.43 and a unit Reynolds number (Re1) of 11.5 [...] Read more.
The paper focuses on the investigation of unsteady effects in shock wave/boundary layer interaction. The study was carried out using a flat plate model subjected to a free stream Mach number of 1.43 and a unit Reynolds number (Re1) of 11.5 × 106 1/m. To generate two-dimensional disturbances in the laminar boundary layer upstream of the separation region, a dielectric barrier discharge was employed. The disturbances were generated within the frequency range of 500 to 1700 Hz. The Strouhal numbers based on the length of the separation bubble ranged from 0.04 to 0.13. The measurements were carried out using a hot-wire anemometer. Analysis of the data shows that disturbances in this frequency range mostly decay. The maximum amplitudes of perturbations were observed at frequencies of 1250 Hz and 1700 Hz. Full article
(This article belongs to the Special Issue Plasma Actuator)
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38 pages, 47469 KiB  
Article
Active Flow Control for Passage Vortex Reduction in a Linear Turbine Cascade with Various Tip Clearance Sizes Using a Dielectric Barrier Discharge Plasma Actuator
by Takayuki Matsunuma and Takehiko Segawa
Aerospace 2023, 10(7), 641; https://doi.org/10.3390/aerospace10070641 - 16 Jul 2023
Cited by 1 | Viewed by 1208
Abstract
In an axial-flow turbine of a jet engine used for aircraft propulsion, the passage vortex (PV) and tip leakage vortex (TLV) generated inside the blade passage deteriorate the aerodynamic performance. In this study, a dielectric barrier discharge plasma actuator (PA) was installed in [...] Read more.
In an axial-flow turbine of a jet engine used for aircraft propulsion, the passage vortex (PV) and tip leakage vortex (TLV) generated inside the blade passage deteriorate the aerodynamic performance. In this study, a dielectric barrier discharge plasma actuator (PA) was installed in the upstream endwall of the turbine cascade to suppress the PV. The effects of the presence or absence of tip clearance and the change in the size of the tip clearance on the vortex structure at the exit of the turbine cascade were observed by recording the flow velocity distributions using particle image velocimetry. In the absence of tip clearance, only the PV existed and was completely suppressed by the PA. By contrast, in the presence of tip clearance, a TLV occurred in addition to the PV. When the input voltage to the PA was varied with various tip clearance sizes, the change in the flow fields where the PV and TLV interfered was clarified. With tip clearance, the PV was suppressed as the input voltage increased; however, the TLV increased considerably. At each tip clearance size, changes in the center positions of the PV and TLV were observed at varying input voltages of the PA. With increasing input voltages of the PA, the center position of the PV moved to the pressure surface side of the tip of the adjacent blade, and the center position of the TLV moved toward the middle of the flow passage. With a larger tip clearance, the amount of movement at the center positions of both the PV and TLV increased. Full article
(This article belongs to the Special Issue Plasma Actuator)
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17 pages, 7523 KiB  
Article
On the Possibility of Cross-Flow Vortex Cancellation by Plasma Actuators
by Amir Abdullaev, Alexander Kotvitskii, Ivan Moralev and Maxim Ustinov
Aerospace 2023, 10(5), 469; https://doi.org/10.3390/aerospace10050469 - 17 May 2023
Cited by 1 | Viewed by 1301
Abstract
Cancellation of the cross-flow vortices in a swept-wing boundary layer is attempted by plasma actuator array in numerical simulation. The response of the boundary layer to the stationary excitation by a single actuator section is measured experimentally and compared to the response obtained [...] Read more.
Cancellation of the cross-flow vortices in a swept-wing boundary layer is attempted by plasma actuator array in numerical simulation. The response of the boundary layer to the stationary excitation by a single actuator section is measured experimentally and compared to the response obtained from the solution to the parabolized stability equations. A linear approach is shown to be held within the peak-to-peak magnitude of the stationary cross-flow vortices below 10% of the local potential flow velocity. Within the linear model, an optimal control strategy and a faster suboptimal one are developed to calculate voltage amplitude distribution across the electrodes, taking into account the forcing constraints. Simulation of the cancellation process is performed, showing up to a 20 dB reduction in the initial spanwise velocity modulation in the boundary layer. The minimal actuator resolution required for the successive implementation of the control is shown to be in the order of a quarter of the most amplified wavelength, or 3–4 displacement thickness of the boundary layer. Linear estimates predict up to a 150 mm (22% of flow acceleration region length) transition delay for an actuator momentum coefficient of 0.005%. Full article
(This article belongs to the Special Issue Plasma Actuator)
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