A Study on the Plasma Actuator Electrode Geometry Configurations for Improvement of the Aerodynamic Performance of an Airfoil

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AKBIYIK, Hürrem ;YAVUZ, Hakan ;AKANSU, Yahya Erkan.
A Study on the Plasma Actuator Electrode Geometry Configurations for Improvement of the Aerodynamic Performance of an Airfoil. 
Strojniški vestnik - Journal of Mechanical Engineering, [S.l.], v. 64, n.12, p. 719-725, november 2018. 
ISSN 0039-2480.
Available at: <https://www.sv-jme.eu/sl/article/a-study-on-the-plasma-actuator-electrode-geometry-configurations-for-improvement-of-the-aerodynamic-performance-of-an-airfoil/>. Date accessed: 07 apr. 2020. 
doi:http://dx.doi.org/10.5545/sv-jme.2017.5041.
Akbıyık, H., Yavuz, H., & Akansu, Y.
(2018).
A Study on the Plasma Actuator Electrode Geometry Configurations for Improvement of the Aerodynamic Performance of an Airfoil.
Strojniški vestnik - Journal of Mechanical Engineering, 64(12), 719-725.
doi:http://dx.doi.org/10.5545/sv-jme.2017.5041
@article{sv-jmesv-jme.2017.5041,
	author = {Hürrem  Akbıyık and Hakan  Yavuz and Yahya Erkan Akansu},
	title = {A Study on the Plasma Actuator Electrode Geometry Configurations for Improvement of the Aerodynamic Performance of an Airfoil},
	journal = {Strojniški vestnik - Journal of Mechanical Engineering},
	volume = {64},
	number = {12},
	year = {2018},
	keywords = {NACA0015 airfoil; lift and drag coefficients; square plasma actuator; sawtooth plasma actuator; linear plasma actuator},
	abstract = {In this study, the induced flow effects of plasma generated by various types of electrode geometry configurations are presented. The model chosen for the study is a NACA0015 airfoil. The experiments are conducted in a wind tunnel at Reynolds number of 4.8×10^4. The plasma actuators mounted on the leading edge of the airfoil at chord position of 0.1 (x/C). The plasma actuators consist of an embedded and exposed electrode between which a dielectric material is placed. The applied voltage is set to 7 kV_pp. The excitation frequency is also set to 3.5 kHz. Three different electrode geometry configurations, namely as linear, saw-tooth and square, are considered for the study. As a part of the experimental study, the two dimensional and three dimensional flow structures generated by the plasma actuators and related analysis results are presented. In addition, necessary measurements are also made to determine the drag and lift forces.},
	issn = {0039-2480},	pages = {719-725},	doi = {10.5545/sv-jme.2017.5041},
	url = {https://www.sv-jme.eu/sl/article/a-study-on-the-plasma-actuator-electrode-geometry-configurations-for-improvement-of-the-aerodynamic-performance-of-an-airfoil/}
}
Akbıyık, H.,Yavuz, H.,Akansu, Y.
2018 November 64. A Study on the Plasma Actuator Electrode Geometry Configurations for Improvement of the Aerodynamic Performance of an Airfoil. Strojniški vestnik - Journal of Mechanical Engineering. [Online] 64:12
%A Akbıyık, Hürrem 
%A Yavuz, Hakan 
%A Akansu, Yahya Erkan
%D 2018
%T A Study on the Plasma Actuator Electrode Geometry Configurations for Improvement of the Aerodynamic Performance of an Airfoil
%B 2018
%9 NACA0015 airfoil; lift and drag coefficients; square plasma actuator; sawtooth plasma actuator; linear plasma actuator
%! A Study on the Plasma Actuator Electrode Geometry Configurations for Improvement of the Aerodynamic Performance of an Airfoil
%K NACA0015 airfoil; lift and drag coefficients; square plasma actuator; sawtooth plasma actuator; linear plasma actuator
%X In this study, the induced flow effects of plasma generated by various types of electrode geometry configurations are presented. The model chosen for the study is a NACA0015 airfoil. The experiments are conducted in a wind tunnel at Reynolds number of 4.8×10^4. The plasma actuators mounted on the leading edge of the airfoil at chord position of 0.1 (x/C). The plasma actuators consist of an embedded and exposed electrode between which a dielectric material is placed. The applied voltage is set to 7 kV_pp. The excitation frequency is also set to 3.5 kHz. Three different electrode geometry configurations, namely as linear, saw-tooth and square, are considered for the study. As a part of the experimental study, the two dimensional and three dimensional flow structures generated by the plasma actuators and related analysis results are presented. In addition, necessary measurements are also made to determine the drag and lift forces.
%U https://www.sv-jme.eu/sl/article/a-study-on-the-plasma-actuator-electrode-geometry-configurations-for-improvement-of-the-aerodynamic-performance-of-an-airfoil/
%0 Journal Article
%R 10.5545/sv-jme.2017.5041
%& 719
%P 7
%J Strojniški vestnik - Journal of Mechanical Engineering
%V 64
%N 12
%@ 0039-2480
%8 2018-11-16
%7 2018-11-16
Akbıyık, Hürrem, Hakan  Yavuz, & Yahya Erkan Akansu.
"A Study on the Plasma Actuator Electrode Geometry Configurations for Improvement of the Aerodynamic Performance of an Airfoil." Strojniški vestnik - Journal of Mechanical Engineering [Online], 64.12 (2018): 719-725. Web.  07 Apr. 2020
TY  - JOUR
AU  - Akbıyık, Hürrem 
AU  - Yavuz, Hakan 
AU  - Akansu, Yahya Erkan
PY  - 2018
TI  - A Study on the Plasma Actuator Electrode Geometry Configurations for Improvement of the Aerodynamic Performance of an Airfoil
JF  - Strojniški vestnik - Journal of Mechanical Engineering
DO  - 10.5545/sv-jme.2017.5041
KW  - NACA0015 airfoil; lift and drag coefficients; square plasma actuator; sawtooth plasma actuator; linear plasma actuator
N2  - In this study, the induced flow effects of plasma generated by various types of electrode geometry configurations are presented. The model chosen for the study is a NACA0015 airfoil. The experiments are conducted in a wind tunnel at Reynolds number of 4.8×10^4. The plasma actuators mounted on the leading edge of the airfoil at chord position of 0.1 (x/C). The plasma actuators consist of an embedded and exposed electrode between which a dielectric material is placed. The applied voltage is set to 7 kV_pp. The excitation frequency is also set to 3.5 kHz. Three different electrode geometry configurations, namely as linear, saw-tooth and square, are considered for the study. As a part of the experimental study, the two dimensional and three dimensional flow structures generated by the plasma actuators and related analysis results are presented. In addition, necessary measurements are also made to determine the drag and lift forces.
UR  - https://www.sv-jme.eu/sl/article/a-study-on-the-plasma-actuator-electrode-geometry-configurations-for-improvement-of-the-aerodynamic-performance-of-an-airfoil/
@article{{sv-jme}{sv-jme.2017.5041},
	author = {Akbıyık, H., Yavuz, H., Akansu, Y.},
	title = {A Study on the Plasma Actuator Electrode Geometry Configurations for Improvement of the Aerodynamic Performance of an Airfoil},
	journal = {Strojniški vestnik - Journal of Mechanical Engineering},
	volume = {64},
	number = {12},
	year = {2018},
	doi = {10.5545/sv-jme.2017.5041},
	url = {https://www.sv-jme.eu/sl/article/a-study-on-the-plasma-actuator-electrode-geometry-configurations-for-improvement-of-the-aerodynamic-performance-of-an-airfoil/}
}
TY  - JOUR
AU  - Akbıyık, Hürrem 
AU  - Yavuz, Hakan 
AU  - Akansu, Yahya Erkan
PY  - 2018/11/16
TI  - A Study on the Plasma Actuator Electrode Geometry Configurations for Improvement of the Aerodynamic Performance of an Airfoil
JF  - Strojniški vestnik - Journal of Mechanical Engineering; Vol 64, No 12 (2018): Strojniški vestnik - Journal of Mechanical Engineering
DO  - 10.5545/sv-jme.2017.5041
KW  - NACA0015 airfoil, lift and drag coefficients, square plasma actuator, sawtooth plasma actuator, linear plasma actuator
N2  - In this study, the induced flow effects of plasma generated by various types of electrode geometry configurations are presented. The model chosen for the study is a NACA0015 airfoil. The experiments are conducted in a wind tunnel at Reynolds number of 4.8×10^4. The plasma actuators mounted on the leading edge of the airfoil at chord position of 0.1 (x/C). The plasma actuators consist of an embedded and exposed electrode between which a dielectric material is placed. The applied voltage is set to 7 kV_pp. The excitation frequency is also set to 3.5 kHz. Three different electrode geometry configurations, namely as linear, saw-tooth and square, are considered for the study. As a part of the experimental study, the two dimensional and three dimensional flow structures generated by the plasma actuators and related analysis results are presented. In addition, necessary measurements are also made to determine the drag and lift forces.
UR  - https://www.sv-jme.eu/sl/article/a-study-on-the-plasma-actuator-electrode-geometry-configurations-for-improvement-of-the-aerodynamic-performance-of-an-airfoil/
Akbıyık, Hürrem, Yavuz, Hakan, AND Akansu, Yahya.
"A Study on the Plasma Actuator Electrode Geometry Configurations for Improvement of the Aerodynamic Performance of an Airfoil" Strojniški vestnik - Journal of Mechanical Engineering [Online], Volume 64 Number 12 (16 November 2018)

Avtorji

Inštitucije

  • Çukurova University, Faculty of Engineering and Architecture, Turkey 1
  • Niğde Ömer Halisdemir University, Faculty of Engineering, Turkey 2

Informacije o papirju

Strojniški vestnik - Journal of Mechanical Engineering 64(2018)12, 719-725

https://doi.org/10.5545/sv-jme.2017.5041

In this study, the induced flow effects of plasma generated by various types of electrode geometry configurations are presented. The model chosen for the study is a NACA0015 airfoil. The experiments are conducted in a wind tunnel at Reynolds number of 4.8×10^4. The plasma actuators mounted on the leading edge of the airfoil at chord position of 0.1 (x/C). The plasma actuators consist of an embedded and exposed electrode between which a dielectric material is placed. The applied voltage is set to 7 kV_pp. The excitation frequency is also set to 3.5 kHz. Three different electrode geometry configurations, namely as linear, saw-tooth and square, are considered for the study. As a part of the experimental study, the two dimensional and three dimensional flow structures generated by the plasma actuators and related analysis results are presented. In addition, necessary measurements are also made to determine the drag and lift forces.

NACA0015 airfoil; lift and drag coefficients; square plasma actuator; sawtooth plasma actuator; linear plasma actuator