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Research Papers: Fundamental Issues and Canonical Flows

# Experimental Study of the Flow Induced by a Sinusoidal Dielectric Barrier Discharge Actuator and Its Effects on a Flat Plate Natural Boundary Layer

[+] Author and Article Information
Pierre Magnier, Vincent Boucinha, Régine Weber, Annie Leroy-Chesneau

Laboratoire de Mécanique et d’Énergétique, 8 Rue Léonard de Vinci, 45072 Orléans, Cedex 02, France

BinJie Dong, Dunpin Hong

GREMI, UMR 6606, CNRS/Université d’Orléans, 14 Rue d’Issoudun BP 6744, 45072 Orléans, Cedex 02, France

J. Fluids Eng 131(1), 011203 (Dec 02, 2008) (11 pages) doi:10.1115/1.3026722 History: Received July 16, 2007; Revised October 09, 2008; Published December 02, 2008

## Abstract

Since the mid-1990s, electrohydrodynamic actuators have been developed for modifying on subsonic airflows. The principle of plasma action is the use of the direct conversion of electrical energy into kinetic energy in order to act on the flow boundary layer. This paper presents our contribution to such an investigation concerning an electrohydrodynamic actuator consisting of several sinusoidal dielectric barrier discharges. First, the ionic wind induced by this actuator was measured with a pressure sensing probe. The induced flow velocity increased with the applied voltage and frequency. The particle image velocimetry system without external airflow showed the presence of induced swirls, generated by the ion movement in plasma. Then the action of this actuator on a flat plate boundary layer in parallel flow at zero incidence was studied in a subsonic wind tunnel. Experiments were performed for 15 m/s and 22 m/s. They showed that electric discharges ($±8$ kV, 1 kHz) acting on a laminar flow tripped the laminar-to-turbulent transition. Moreover, higher applied voltages (up to $±12$ kV, 1 kHz) were necessary for modifying turbulent boundary layers.

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## Figures

Figure 1

Actuator with several dielectric barrier discharges

Figure 2

Power supply for the DBD actuator

Figure 3

Voltage and current versus time (±5 kV, 1 kHz)

Figure 4

Schematic of the flat plate with positions of four DBD actuators

Figure 5

Subsonic wind tunnel with a square test section of 50 cm×50 cm×2 m

Figure 6

Actuator temperature increase during its activation duration (initial actuator temperature of 22°C)

Figure 7

Induced flow velocity, 1 mm after the last electrode (a) for various frequencies (0.5 kHz, 1 kHz, and 2 kHz) and a given applied voltage of ±8 kV, and (b) for various high voltages (from ±6 kV to 12 kV) and a given frequency of 1 kHz

Figure 8

Flow streamlines induced by the DBD actuator with a frequency of 1 kHz and a voltage of (a) ±5 kV and (b) ±12 kV

Figure 9

Schematic of the flow induced by a DBD actuator

Figure 10

Nondimensional mean velocity profiles for 15 m/s and 22 m/s, without and with actuator 1 activated (±8 kV, 1 kHz), in s=155 mm, 187 mm, and 427 mm

Figure 11

u+ velocity profiles for 15 m/s and 22 m/s, without and with actuator 1 activated (±8 kV, 1 kHz), in s=155 mm, 187 mm, and 427 mm

Figure 12

Boundary layer thickness δ99 (mm) along the flat plate for 15 m/s and 22 m/s, for various DBD actuator positions (±8 kV, 1 kHz)

Figure 13

Displacement thickness δ1 (mm) along the flat plate for 15 m/s and 22 m/s, for various DBD actuator positions (±8 kV, 1 kHz)

Figure 14

Momentum thickness δ2 (mm) along the flat plate for 15 m/s and 22 m/s, for various DBD actuator positions (±8 kV, 1 kHz)

Figure 15

Shape factor H along the flat plate for 15 m/s and 22 m/s, for various DBD actuator positions (±8 kV, 1 kHz)

Figure 16

Drag D (mN) along the flat plate for 15 m/s and 22 m/s, for various DBD actuator positions (±8 kV, 1 kHz)

Figure 17

Velocity profiles for 22 m/s, without and with actuator 2 activated (±8 kV, 1 kHz), in s=315 mm and 463 mm

Figure 18

Velocity profiles in s=446 mm for 15 m/s, with promoted transition, without and with actuator 3 activated (from ±8 kV to ±12 kV, 1 kHz)

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