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1

Application of Plasma Actuator with Two Mesh Electrodes to Active Control of Boundary Layer at 50 Hz Power Supply

Gnapowski Ernest, Pytka Jarosław, Gnapowski Sebastian, Józwik Jerzy, Tomiło Paweł

Advances in Science and Technology. Research Journal

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2023

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Vol. 17, no 1

58--63

EN

Numerous studies are conducted to improve the flow in the boundary layer to ensure laminar flow and in particular to increase flight safety. A new solution used to improve the laminar flow is the plasma actuator. The classic configuration of DBD plasma actuators is commonly used with the asymmetric electrode system. The manuscript describes the results of tests with a plasma actuator. Experimental tests were carried out on the built model of the wing with the SD 7003 profile, a plasma actuator was mounted on the upper surface. In contrast to the commonly used solution with solid tape copper electrodes, the novelty in the described research in the manuscript is the use of a large GND electrode (covering 70% of the upper surface of the wing) and a HV mesh electrode. The use of a plasma actuator on the upper surface of the wing affects the air flow in the boundary layer as a result of air ionization. The tests were carried out for a supply voltage from V = 7.0 kV to 12 kV and Reynolds number, Re = 87500 to 240000, flow velocity during the tests in the tunnel was in the range of U = 5-15 m/s and the angle of attack α = 5 -15 degrees. On the basis of the results experimental tests, the percentage change in the lift coefficient was calculated for the switched on and off DBD system. The obtained results indicate a maximum 17% increase in the lift coefficient for the plasma actuator activated for air flow U = 5 m/s and angle of attack α = 5 degrees. In the remaining configurations, changes in the lift coefficient amounted to 4%.

2

Review of Selected Methods for Increasing the Aerodynamic Force of the Wing

Gnapowski Ernest

Advances in Science and Technology. Research Journal

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2019

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Vol. 13, no 1

60--67

EN

The manuscript presents the methods of increasing the aerodynamic force of the airfoil, currently used in aviation, and the directions of further research development. Currently, several methods are known and used to increase the aerodynamic force of the airfoil. The most widespread ones include wing mechanization systems, among others, flaps and slats. The non-mechanical elements of the wing construction that enable to increase the carrying force are used as well, among others; wing cuffs, vortilons, vortex generator. Research is being carried out on the introduction of mechanical elements that increase the lift force (Continuous Trailing Edge Flap, Morphing Wing), as well as non-mechanical elements such as plasma actuators. The manuscript describes the selected non-mechanical and mechanical elements currently used to increase the lift and the directions for the development of further research on increasing the aerodynamic force.

3

Plasma Actuator with Two Mesh Electrodes to Control the Flow Boundary Layer

Gnapowski Ernest

Advances in Science and Technology. Research Journal

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2019

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Vol. 13, no 2

31--37

EN

The manuscript presents selected designs of Dielectric Barrier Discharge (DBD) plasma actuators used to control the flow of the boundary layer on the surface of the wing. The principle of DBD plasma actuator operation and the process of the “ion wind” formation are presented. The manuscript presents the results of the tests carried out on the sash model with the SD 7003 profile and a DBD plasma actuator with two mesh electrodes, for which tests were carried out and tunnel images were recorded.

4

Numerical modeling of plasma Actuator at high pressure

Mekri A., Boukreris A., Kraloua B., Hennad A.

Przegląd Elektrotechniczny

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2018

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R. 94, nr 4

34--38

EN

In this work, we develop a physical model for an asymmetric dielectric barrier discharge (DBD) in air driven by nanosecond voltage negative pulse. This configuration has been proposed as actuators for flow control. We present a hydrodynamic model to approximate the evolution of charge densities. The model consists of the continuity equations for electrons, positive and negative ions coupled to Poisson’s equation for the electric field. We use Scharfetter and Gummel schemes SG and SG0 schemes coupling at time splitting method to resolve the transport equations system. The Poisson's equation is resolved by the tridiagonal method coupled with the over-relaxation method to calculate the electrical field. The stationary spatial distribution of the electron and ion densities, the electric potential, and the electric field in a two-dimensional (2D) configuration are presented.

PL

W pracy przedstawiono model fizyczny asymetrycznego wyładowania barierowego dielektrycznego (DBD) napędzanego impulsem negatywnym nano-nanocząsteczkowym w powietrzu. Konfiguracja została zaproponowana jako siłowniki do sterowania przepływem. Przedstawiono model hydrodynamiczny przybliżający ewolucję gęstości ładunku. Model składa się z równań ciągłości dla elektronów, jonów dodatnich i ujemnych sprzężonych z równaniem Poissona dla pola elektrycznego. Używano schematy Scharfettera i Gummla Przedstawiono stacjonarny rozkład przestrzenny gęstości elektronów i jonów, potencjał elektryczny oraz pole elektryczne w konfiguracji dwuwymiarowej (2D).

5

Experimental study of flow control over an Ahmed body using plasma actuator

Shadmani S., Mousavi Nainiyan S. M, Ghasemiasl R., Mirzaei M., Pouryoussefi S. G.

Mechanics and Mechanical Engineering

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2018

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Vol. 22, nr 1

239--251

EN

Ahmed Body is a standard and simplified shape of a road vehicle that’s rear part has an important role in flow structure and it’s drag force. In this paper flow control around the Ahmed body with the rear slant angle of 25° studied by using the plasma actuator system situated in middle of the rear slant surface. Experiments conducted in a wind tunnel in two free stream velocities of U = 10 m/s and U = 20 m/s using steady and unsteady excitations. Pressure distribution and total drag force was measured and smoke flow visualization carried out in this study. The results showed that at U = 10 m/s using plasma actuator suppress the separated flow over the rear slant slightly and be effective on pressure distribution. Also total drag force reduces in steady and unsteady excitations for 3.65% and 2.44%, respectively. At U = 20 m/s, using plasma actuator had no serious effect on the pressure distribution and total drag force.

6

Experimental study of flow control over a standard road vehicle using plasma actuator

Shadmani S., Mousavi Nainiyan S. M., Ghasemiasl R., Mirzaei M., Pouryoussefi S. G.

Mechanics and Mechanical Engineering

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2018

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Vol. 22, nr 4

1047--1059

EN

Ahmed Body is a standard and simplified shape of a road vehicle that's rear part has an important role in flow structure and it's drag force. In this paper flow control around the Ahmed body with the rear slant angle of 25˚ studied by using the plasma actuator system situated in middle of the rear slant surface. Experiments conducted in a wind tunnel in two free stream velocities of U = 10m/s and U = 20m/s using steady and unsteady excitations. Pressure distribution and total drag force were measured and smoke flow visualization carried out in this study. The results showed that at U = 10m/s using plasma actuator suppress the separated flow over the rear slant slightly and be effective on pressure distribution. Also, total drag force reduces in steady and unsteady excitations for 3.65% and 2.44%, respectively. At U = 20m/s, using plasma actuator had no serious effect on the pressure distribution and total drag force.

7

Optical emission spectroscopy investigation of the low-power multispark plasma actuator

Olszewski S., Bondarenko P., Kostenko S., Komada P.

Elektronika : konstrukcje, technologie, zastosowania

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2013

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Vol. 54, nr 8

54-57

PL

Jedną z istotnych metod kontrolowania przepływu aerodynamicznego przy powierzchni jest oddziaływanie na przepływ pulsującej plazmy. Dla rzeczywistych urządzeń wyładowczych, stosowanych w tego rodzaju zagadnieniach bardzo ważne jest zrozumienie jakie tryby zachowania plazmy z ciśnieniem atmosferycznym dają maksymalny efekt przy minimalnym zużyciu energii. Praktyczny aspekt pracy stanowią wyniki postępów w pracach nad skalowalnym wysokonapięciowym źródłem zasilania do wytwarzania wieloiskrowych wyładowań o dużej długości całkowitej. Podstawowy aspekt pracy stanowią rezultaty badań właściwości emisji plazmy dla quasi-stacjonarnych wioeloiskrowych wyładowań w ciśnieniu atmosferycznym.

EN

One of the important ways of controlling aerodynamic flow near the surface there is an impact to the flow of pulsating plasma. For a real discharge devices used in such problems it is very important to understand what modes maintain plasma of atmospheric pressure give maximum effect with minimum energy consumption. In the applied aspect of this work presents the results of the development of a scalable high-voltage power source to generate a multi-spark discharge with large total length. A fundamental aspect of this work presents the results of research of the plasma emission properties of quasi-stationary multi-spark discharge in atmospheric pressure.

8

Multi - DBD actuator with floating inter - electrode for aerodynamic control

Berendt A., Podliński J., Mizeraczyk J.

Nukleonika

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2012

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Vol. 57, No. 2

249-252

EN

In this paper the use of a floating inter-electrode in a multi-DBD (dielectric barrier discharge) plasma actuator is described. The multi-DBD plasma actuators with floating inter-electrodes were investigated to get a longer DBD on a dielectric surface and to maximise generated net airflow. Our actuator was used to control the boundary layer flow separation around NACA0012 airfoil model. The results of our investigations suggests that multi-DBD actuators with floating inter-electrodes can be attractive for aerodynamic purposes.