بررسی تجربی هندسه های مختلف مولدهای پلاسماییِ جریان گردابه ای در کنترل جریان تراکم پذیر

نوع مقاله : مقاله پژوهشی

نویسندگان

1 دانشجوی دکتری / دانشکده مهندسی هوافضا، دانشگاه صنعتی امیرکبیر، تهران

2 عضو هیات علمی / دانشکده مهندسی هوافضا، دانشگاه صنعتی امیرکبیر، تهران

چکیده

توانایی چهار هندسه‌ی مختلف مولد پلاسمایی جریان گردابه‌ای (شانه‌ای، T شکل، دندانه اره‌ای ساده و دندانه اره‌ای مشبک) در کنترل جریان تراکم پذیر به طور تجربی در ولتاژ و فرکانس های عملکردی مختلف بر روی یک ایرفویل فوق بحرانی بررسی و موارد استفاده از هر کدام توصیه شده است. از تجزیه و تحلیل نمودار چگالی طیفی توان مربوط به نوسانات فشار در لایه مرزی برای تعیین فرکانس‌های تحریک ناپایای عملگرهای پلاسمایی استفاده و مشخص شد وجود فرکانس غالب در نمودارهای چگالی طیفی توان نشانه‌ی بارزی بر وجود جدایی جریان در آن منطقه از ایرفویل می باشد. در آزمایشها مشاهده شد که در هنگام عملکرد پالسی عملگرهای پلاسمایی با هندسه شانه‌ای، در جلوی عملگر حباب جدایی ایجاد می شود که استفاده از هندسه‌یT شکل، اندازه حباب جدایی را کاهش می دهد. بر اساس نتیجه‌ی آزمایشها، عملگرهای پلاسمایی T شکل و دندانه اره‌ای مشبک با عملکرد پالسی، در قیاس با هندسه‌های شانه‌ای و دندانه اره‌ای ساده در شرایط یکسان کارایی بیشتری در کنترل جریان تراکم‌پذیر دارند.

کلیدواژه‌ها


عنوان مقاله [English]

Experimental Investigation of Different Plasma Vortex Generator Configurations for Compressible Flow Control

نویسندگان [English]

  • Alireza Ghayour 1
  • Mahmoud Mani 2
  • Mohammad Saeedi 2
1 Aerospace Engineering Department., Amirkabir University of Technology
2 Faculty member/ Amirkabir University of Technology
چکیده [English]

In the current research, four different configurations of plasma streamwise vortex generators (PSVGs) for compressible flow control have been experimentally investigated to analyze their capabilities in controlling compressible flow (M=0.428) at the different excitation voltages and frequencies. The impacts of electrical parameters on the performance and efficiency of plasma actuators have been studied. Power spectrum analysis of pressure fluctuations in the boundary layer has been employed to determine the unsteady forcing frequencies of PSVGs. The presence of a dominant frequency in power spectrum diagrams is a strong indication of flow separation in the region from which the pressure signal has been extracted. As such, it was observed that the separation bubble was created in front of the comb-type PSVG when it starts its operation; however, using the T-type configuration diminished the separation bubble. T-type and mesh-type PSVGs, in similar experimental conditions, were observed to be more efficient than the comb-type and saw-type geometries in controlling compressible flow.

کلیدواژه‌ها [English]

  • Plasma Actuator
  • flow control
  • unsteady forcing frequency
  • plasma vortex generator
[1] P. Bowles, "Wind tunnel experiments on the effect of compressibility on the attributes of dynamic stall," University of Notre Dame, South Bend, Notre Dame, March 2012.
[2] Thomas, F., Corke, C., Iqbal, M., Kozlov, A. and Schatzman, D., "Optimization of dielectric barrier discharge plasma actuators for active aerodynamic flow control," AIAA, Vols. 47, No. 9, pp. 2169-2178, 2009.
[3] Giepman, R. H. M., and Kotsonis, M., "On the mechanical efficiency of dielectric barrier discharge plasma actuators," Applied Physics Letters, vol. 98, 2011.
[4] Ying-hong, L. Yun, W. Hui-min, S., Hua, L. and Min, J., "Plasma Flow Control," InTech, Shanghai, 2011.
[5] Asada, K. , Yoshihiko, N., Akira, O. and Kozo, F., "Airfoil Flow Experiment on the Duty Cycle of DBD Plasma Actuator," in 47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition, Orlando, Florida, 2009.
[6] K. Fujii, "High-performance computing-based exploration of flow control with micro devices," Philosophical transactions of the royal society A, vol. A, pp. 1-13, 2017.
[7] Hikaru, A., Satoshi, S., Makoto, S., Aiko, Y., Taku, N. and Kozo, F., "Computational and experimental analysis of flow structures induced by a plasma actuator with burst modulations in quiescent air," Mechanical Engineering Journal, vol. 2, 2015.
[8] Enloe, C., McLaughlin, T., VanDyken, R., Kachner, K., Jumper, E., Corke, C., Post, M. and Haddad, O., "Mechanisms and Responses of a Single Dielectric Barrier Plasma Actuator: Geometric Effects," AIAA Journal, Vols. 42, no. 3, pp. 595-604, 2004.
[9] Rodrigues, F., Pascoa, J. and Trancossi, M., "Analysis of Innovative Plasma Actuator Geometries for Boundary Layer Control," in ASME, Phoenix, Arizona, 2016.
[10] Timothy, N., Takehiko, S. and Hirohide, F., "Flow Control on a NACA 4418 Using Dielectric-Barrier-Discharge Vortex Generator," AIAA, vol. 51, pp. 452-465, February 2013.
[11] Chuan, H. and Thomas, C., "Numerical and Experimental Analysis of Plasma Flow Control Over a Hump Model," in 45th Aerospace Sciences Meeting, January 8-11,, Reno, Nevada, 2007.
[12] Michael, W., Flint, O. and David, S., "A Parametric Investigation of Plasma Streamwise Vortex Generator Performance," in 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Notre Dame, 2012.
[13] Ghayour, A., Mani, M., "Experimental investigation of plasma vortex generator in flow control," Aircraft Engineering and Aerospace Technology, 2019.
[14] Berendt, A., Podlinski, J., and Mizeraczyk, J., "Comparison of airflow patterns produced by dbd actuators with smooth or saw-like discharge electrode," Journal of Physics: Conference Series, 2011.
[15] Zhifeng, L., Mingming, Z. and Lianze, W., "Investigation on 3D flow field induced by a plasma actuator with serrated electrode," Science bulletin, pp. 481-487, March 2016.
[16] Zhang, P., Dai, C., Liu, A. and Wang, J., "The effect of actuation frequency on the plasma synthetic jet," SCIENCE CHINA, vol. 54, p. 2945–2950, 2011.
[17] A. Santhanakrishnan, "Characterization and flow physics of plasma synthetic jet actuators," University of Kentucky, Kentucky, 2007.
[18] Jae-San, Y., Jae-Hung, H. and Ho-young, K., "Flow control technology for vibration load reduction," January 2013. [Online]. Available: http://sss.kaist.ac.kr/?page_id=2915.
[19] Ronald, E. and Philippe, L., "Effect of Plasma Actuator Excitation for Controlling Bypass Transition in Boundary Layers," in AIAA, Orlando, Florida, 2010.
[20] Bal Krishan, M. and Panigrahi, P., "Formation and characterization of the vortices generated by a DBD plasma actuator in burst mode," Physics of Fluids, vol. 29, 2017.
[21] Chi Wai, W., Xiaoqi, C.,Qian, P. and Yu, Z., "Effects of plasma actuator generated vortices on a turbulent boundary layer," in 10th International Symposium on Turbulence and Shear Flow Phenomena (TSFP10), Chicago, USA, 2017.
[22] H. Chuan, "Plasma slats flaps; an application ofplasma actuators for hingeless aerodinamic control," University of Notre Dame, Notre Dame, 2008.
[23] Timothy, N. and Kwing-So, C., "Dielectric-barrier-discharge vortex generators: characterisation and optimisation for flow separation control," Springer, vol. 52, no. Springer-Verlag, p. 329–345, 2012.
[24] Benard, N., Moreau, E. and Balcon, N., "Electric wind produced by a surface dielectric barrier discharge operating over a wide range of relative humidity,," in 47th AIAA Aerospace Sciences Meeting,, 2009.
[25] Rizzetta, D. and Visbal, M., "Effect of compressibility on plasma-based transition control for a wing with leading-edge excrescence," INTERNATIONAL JOURNAL OF COMPUTATIONAL FLUID DYNAMICS, vol. 31, pp. 156-173, 2017.
[26] M. Denison, "Compressibility Effects on the Non-Linear Receptivity of Boundary Layers to Dielectric Barrier Discharges," The University of Texas at Arlington, TEXAS, 2013.
[27] C. Rethmel, "Airfoil Leading Edge Flow Separation Control Using Nanosecond Pulse DBD Plasma Actuators," The Ohio State University, Ohio State, 2011.
[28] Little, J., Takashima, K., Nishihara, M., Adamovich, I., and Samimy, M., "High Lift Airfoil Leading Edge Separation Control with Nanosecond Pulse Driven DBD Plasma Actuators," AIAA, 2010.
[29] Frankhouser, M., "Nanosecond Dielectric Barrier Discharge Plasma Actuator Flow Control of Compressible Dynamic Stall," The Ohio State University, Ohio State, 2015.
[30] G. Bradley, "Active control of massively separated high speed /base flow with electricarc arc plasma actuators," University of Illinois at Urbana, Urbana, Illinois, 2012.
[31] W. Matthew, "Nanosecond Dielectric Barrier Discharge Plasma Actuator Flow Control of Compressible Dynamic Stall," The Ohio State University, Ohio State, 2015.
[32] L. Kelley, "Airfoil leading and tralling edge separation control using SDBD plasma actuators," University of Notre Dame, Notre Dame, 2013.
[33] Kwing-So, C., Timothy, N. and Richard, D., "Plasma Virtual Actuators for Flow Control," Journal of Flow Control, Measurement & Visualization, vol. 3, pp. 22-34, 2015.
[34] Philipp, C. and Markus, J., "Numerical Investigations on Tollmien–Schlichting Wave Attenuation Using Plasma-Actuator Vortex Generators," AIAA, pp. 1-7, 2018.
[35] Liu, Z., Wang, L. and Fu, S., "Study of flow induced by sine wave and saw tooth plasma actuators," Science China Physics, Mechanics and Astronomy, 2011.
[36] Durscher, R. and Roy, S., "Three-dimensional flow measurements induced from serpentine plasma actuators in quiescent air," Journal of Physics D: Applied Physics, vol. 45, 2012.
[37] P. Bennani, "Development and optimization of synthetic jets for active flow control," Isae, Toulouse, 2011.
[38] Hikaru, A., Yoshiaki, A., "Flow control using a DBD plasma actuator for horizontal axis wind turbine blades of simple experimental model," in 11th World Congress on Computational Mechanics (WCCM XI), Barcelona, Spain, 2014.
[39] P. Bowles, "Wind tunnel experiments on the effect of compressibility on the attributes of dynamic stall," University of Notre Dame, South Bend, PhD Thesis, Notre Dame, March 2012.