Experimental Study of Using Dielectric Barrier Discharge(DBD) Plasma Actuator as Virtual Winglet

Authors

1 میدان آزادی، ابتدای بزرگراه شهید لشگری، منازل سازمانی شهید فکوری، بلوک 19، طبقه 3، واحد 7

2 AUT

3 MUT

10.22044/jsfm.2024.13888.3815

Abstract

Flow control to reduce drag and increase drag and finally increase the ratio of drag to drag (L/D) has always been the focus of aerodynamic scientists. There are many methods to reduce induced drag. The use of DBD plasma operators is one of the newest methods in reducing induced drag. In this research, in order to investigate the performance of DBD plasma actuators, six configurations of plasma actuators have been used as virtual winglets. Experiments have been performed on the wing with the NACA0012 airfoil. These experiments have been carried out in two Reynolds numbers 150,000 and 300,000 and in two voltages, 6 kV and 10 kV and different angles of attack. The results of this research show that the use of this type of plasma actuator at the tip of the wing as a virtual winglet can increase the lift to drag ratio by about 25% in some cases and the use of two small circular and large linear configurations. respectively, they have the best performance compared to other models for use as a virtual winglet.

Keywords

Main Subjects

References

[1] Anderson JD (2010) Fundamentals of aerodynamics.        Tata McGraw-Hill Education.
[2] Sanket YSG, Joshi N (2016) A Review on Active and Passive Flow Control Techniques," Int. J. Recent Techno. Mech. Elec. Engin. ISSN: 2349-7947, 3(4).
[3] Enloe C, McLaughlin T, VanDyken R, Kachner K, Jumper E, Corke T (2004) Mechanisms and Responses of a Single Dielectric Barrier Plasma Actuator: Geometric Effects, AIAA J., 42(3): 595-604.
 [4] Gregory J, Enloe C, Forte G, McLaughlin T (2007) Force Production Mechanisms of a Dielectric-Barrier Discharge Plasma Actuator , AIAA , The 45th Aerospace Sciences Meeting, Reno, Nevada.
 [5] Kim W, Do H, Mungal G, Cappelli M (2007) On the Role of Oxygen in Dielectric Barrier Discharge Actuation of Aerodynamic Flows , Applied Physics Letters, 91(18):181501-20.
 [6] Lemire S, & Vo HD (2011) Reduction of fan and compressor wake defect using plasma actuation for tonal noise reduction. J. of Turbomachinery, 133(1).
[7] Post M, & Corke T (2004) Separation control using plasma actuators-stationary & oscillating airfoils. In 42nd AIAA Aerospace Sciences Meeting and Exhibit, 841.
 [8] Corke T, Post M (2005) Overview of plasma flow control: concepts, optimization, and applications. 43rd AIAA Aerospace Sciences Meeting and Exhibit.
 [9]  Huang J, Corke TC, Thomas FO (2006) Unsteady plasma actuators for separation control of low-pressure turbine blades. J., 44(7):1477-1487.
[10] Grundmann S, Tropea C (2009) Experimental damping of boundary-layer oscillations using DBD plasma actuators. Int. J. Heat Fluid Flow, 30(3):394-402.
 [11] Jolibois J, Forte M, Moreau, E (2008) Application of an AC barrier discharge actuator to control airflow separation above a NACA 0015 airfoil: Optimization of the actuation location along the chord. J. Electrostat., 66(9-10):496-503.
[12] Kengo A. et al. (2009)Airfoil flow experiment on the duty cycle of DBD plasma actuator. 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition.
 [13] Xiaofei X, et al. (2010) Turbulent Boundary Layer Separation Control by Using DBD Plasma Actuators: Part I—Experimental Investigation. ASME 2010 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers.
 [14] Gabriele N, et al. (2012) Experimental results in DBD plasma actuators for air flow control. IEEE Transactions on Plasma Science, 40(6):1678-1687.
 [15] Miyakawa Y, et al. (2017) Experimental Study on the Detailed Structure of Separation Bubble in Flow Control with DBD Plasma Actuator. 47th AIAA Fluid Dynamics Conference.
[16] Iranshahi JA, Mani K (2018) Dielectric Barrier Discharge Actuators Employed as Alternative to Conventional High-Lift Devices. J. Aircraft, 55(5):2104-2113.
[17] Güler AA, Seyhan M, Akansu YE (2018) Effect of signal modulation of DBD plasma actuator on flow control around NACA 0015. J. Therm. Sci. Techno., 38(1):.95-105.
[18] Taleghani SA, Shaderam A, Mirzaei MS. Abdolahipour S (2018) Parametric study of a plasma actuator at unsteady actuation by measurements of the induced flow velocity for flow control, J. of the Brazilian Society of Mechanical Sciences and Engineering, 40(4):173.
[19]  Hu X, Gao C, Hao J, Zhang Z, Xue M, Yan R (2019) Experimental study of rotor flow separation control using a new type of dielectric barrier discharge plasma actuator, J. Therm. Sci., 28(2):354-359.
[20] Ahmadpour Roudsari M, Parhizkar H, Poryoussefi GH, Tarabi A (2018) Numerical investigation of factors affecting in the steady and unsteady plasma actuators performance on the airflow through the flat plate, Modares Mechanical Engineering, 18(01):111-121. (in Persian)
[21] Sato S,  Furukawa H, Komuro A, Takahashi M, Ohnishi N (2019) Successively accelerated ionic wind with integrated dielectric-barrier-discharge plasma actuator for low-voltage operation, J. Nature, Sci. Reports, 9.1(5813)1-11.
[22] Dhileep K, Arunvinthan S, Pillai SN (2019) Aerodynamic Characteristics of Semi-spiroid Winglets at Subsonic Speed. In Innovative Design, Analysis and Development Practices in Aerospace and Automotive Engineering (I-DAD 2018) (pp. 217-224). Springer, Singapore.
[23] Boesch G, Vo HD, Savard B, Wanko-Tchatchouang C, Mureithi NW (2010) Flight control using wing-tip plasma actuation. J. of aircraft, 47(6):1836-1846.
[24] Hasebe H, Naka Y, Fukagata K (2011) An attempt for suppression of wing-tip vortex using plasma actuators. J. Flu. Sci. Techno., 6(6):976-988.
[25] Agibalova SA, Moralev IA, Saveliev AS, Golub VV (2012) Wing tip vortex Attenuation by plasma actuator. In 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference.
[26] Mizunuma H, Obara H, Segawa T (2013) Flow characteristics induced by winglet-type plasma actuators. J. Flu.Sc. Techno., 8(3):96-406.
[27] Mukut AM, Mizunuma I, Hiromichi H O, Segawa T (2015) Winglet type dielectric barrier discharge plasma actuators: performance characterization and numerical comparison. Procedia Engineering, 105(250-2).
[28] Ayuso L, Sant R, & Meseguer J (2010) Aerodynamic study of airfoils with leading edge imperfections at low Reynolds number. In 40th Fluid Dynamics Conference and Exhibit, p. 4625.
 
Journal of Solid and Fluid Mechanics
Volume 14, Issue 1
March and April 2024
Pages 77-92

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