Wind Tunnel Testing of Plasma Actuator with Two Mesh Electrodes to Boundary Layer Control at High Angle of Attack

Gnapowski, Ernest; Pytka, Jarosław; Jóźwik, Jerzy; Laskowski, Jan; Michalowska, Joanna

doi:10.3390/s21020363

Cited by 3 publications

(1 citation statement)

References 34 publications

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“…The use of a new technology using DBD (Dielectric Barrier Discharge) to change the fl ow in the Applicatio n of Plasma Actuator with Two Mesh Electrodes to Active Control of Boundary Layer at 50 Hz Power Supply Ernest Gnapowski 1* , Jarosław Pytka 2 , Sebastian Gnapowski 3 , Jerzy Józwik 2 , Paweł Tomiło boundary layer is a relatively new solution [1,2]. The construction of the DBD plasma actuator is not very complicated.…”

Section: Introductionmentioning

confidence: 99%

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

Gnapowski¹,

Pytka²,

Gnapowski³

et al. 2023

Adv. Sci. Technol. Res. J.

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Numerous studies are conducted to improve the fl ow in the boundary layer to ensure laminar fl ow and in particular to increase fl ight safety. A new solution used to improve the laminar fl ow is the plasma actuator. The classic confi guration 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 profi le, 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 aff ects the air fl ow 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, R e = 87500 to 240000, fl ow 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 coeffi cient was calculated for the switched on and off DBD system. The obtained results indicate a maximum 17% increase in the lift coeffi cient for the plasma actuator activated for air fl ow U = 5 m/s and angle of attack α = 5 degrees. In the remaining confi gurations, changes in the lift coeffi cient amounted to 4%.

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Section: Introductionmentioning

confidence: 99%

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

Gnapowski¹,

Pytka²,

Gnapowski³

et al. 2023

Adv. Sci. Technol. Res. J.

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The Effect of a Large Grounded Mesh Electrode and Two Types oF High-voltage (HV) Electrodes on Boundary Layer Control

Gnapowski,

Pytka

et al. 2024

2024 11th International Workshop on Metrology for AeroSpace (MetroAeroSpace)

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Characterization, Design Testing and Numerical Modeling of a Subsonic-Low Speed Wind Tunnel

Lara

Salazar

2022

Ing.

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Context: Wind tunnels are essential devices in the study of flow properties through objects and scaled prototypes. This work presents a numerical study to characterize an existing wind tunnel, proposing modifications with the aim to improve the quality of the flow in the test chamber. Method: Experimental measurements of the inlet velocity and pressure distribution of a wind tunnel are nperformed. These empirical values are used as parameters to define boundary conditions in simulations. The Finite Element Method (FEM) at low speeds is implemented to determine the stream function by using a standard Galerkin method. Polynomial interpolations are employed to modify the contraction section design, and numerical simulations are performed in order to compare the numerical results of the flow for the existing and the modified wind tunnels. Results: Experimental measurements of the flow at the wind tunnel entrance are presented. The velocity field and distribution of thermodynamic variables inside the tunnel are numerically determined. This computations are useful since it is experimentally difficult to make measurements inside the channel. Additionally, numerical calculations of these variables are presented under modifications in the tunnel geometry. Conclusions: A comparison between these simulations show that laminar flow at low velocities can be modeled as incompressible and irrotational fluid under a bidimensional approximation along its longitudinal section. It is observed that modifications in the geometry of the tunnel can improve the flow in the test section of the wind tunnel in the laminar regime.

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Wind Tunnel Testing of Plasma Actuator with Two Mesh Electrodes to Boundary Layer Control at High Angle of Attack

Cited by 3 publications

References 34 publications

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

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

The Effect of a Large Grounded Mesh Electrode and Two Types oF High-voltage (HV) Electrodes on Boundary Layer Control

Characterization, Design Testing and Numerical Modeling of a Subsonic-Low Speed Wind Tunnel

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