Next Article in Journal
Thermal and Geometric Error Compensation Approach for an Optical Linear Encoder
Next Article in Special Issue
Nonlinear Control Strategies for an Autonomous Wing-In-Ground-Effect Vehicle
Previous Article in Journal
Design and Fabrication of a High-Speed Atomic Force Microscope Scan-Head
 
 
Search for Articles:
Title / Keyword
Author / Affiliation / Email
Journal
Article Type
 
 
Advanced Search
 
Section
Special Issue
Volume
Issue
Number
Page
 
Journals
Sensors
Volume 21
Issue 2
10.3390/s21020363
sensors-logo
Submit to this Journal Review for this Journal Propose a Special Issue
► Article Menu

Article Menu

share Share announcement Help format_quote Cite question_answer Discuss in SciProfiles
first_page
settings
Order Article Reprints
Font Type:
Arial Georgia Verdana
Font Size:
Aa Aa Aa
Line Spacing:
Column Width:
Background:
Communication

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

by
Ernest Gnapowski
1,*,
Jarosław Pytka
2,
Jerzy Józwik
2,
Jan Laskowski
3 and
Joanna Michałowska
4
1
Faculty of Technical Sciences, University College of Enterprise and Administration, 20-150 Lublin, Poland
2
Faculty of Mechanical Engineering, Lublin University of Technology, 20-618 Lublin, Poland
3
Faculty of Management, Lublin University of Technology, 20-618 Lublin, Poland
4
The Institute of Technical Sciences and Aviation, The State School of Higher Education, 22-100 Chełm, Poland
*
Author to whom correspondence should be addressed.
†
This paper is an extended version of our paper published in: Gnapowski, E.; Pytka, J.; Józwik, J.; Michałowska, J. Wind Tunnel Testing of Mesh Electrodes Plasma Actuator. In Proceedings of the 7th IEEE Workshop on Metrology for AeroSpace, Pisa, Italy, 22–24 June 2020.
Sensors 2021, 21(2), 363; https://doi.org/10.3390/s21020363
Submission received: 3 December 2020 / Revised: 27 December 2020 / Accepted: 4 January 2021 / Published: 7 January 2021
(This article belongs to the Special Issue Sensors in Aircraft)
Browse Figures
Review Reports Versions Notes

Abstract

:
The manuscript presents experimental research carried out on the wing model with the SD 7003 profile. A plasma actuator with DBD (Dielectric Barrier Discharge) discharges was placed on the wing surface to control boundary layer. The experimental tests were carried out in the AeroLab wind tunnel where the forces acting on the wing during the tests were measured. The conducted experimental research concerns the analysis of the phenomena that take place on the surface of the wing with the DBD plasma actuator turned off and on. The plasma actuator used during the experimental tests has a different structure compared to the classic plasma actuator. The commonly tested plasma actuator uses solid/impermeable electrodes, while in the research, the plasma actuator uses a new type of electrodes, two mesh electrodes separated by an impermeable Kapton dielectric. The experimental research was carried out for the angle of attack α = 15° and several air velocities V = 5–15 m/s with a step of 5 m/s for the Reynolds number Re = 87,500–262,500. The critical angle of attack at which the SD 7003 profile has the maximum lift coefficient is about 11°; during the experimental research, the angle was 15°. Despite the high angle of attack, it was possible to increase the lift coefficient. The use of a plasma actuator with two mesh electrodes allowed to increase the lift by 5%, even at a high angle of attack. During experimental research used high voltage power supply for powering the DBD plasma actuator in the voltage range from 7.5 to 15 kV.

1. Introduction

Guaranteeing a high level of aircraft safety requires many experimental tests of the aircraft’s components, including: landing gear [1,2,3,4], wings [5] and other components [6]. The manuscript presents and describes selected designs of DBD (Dielectric Barrier Discharge) plasma actuators, allowing us to increase flight safety by increasing the lift force. Plasma actuators DBD allow us to control the air flow in the boundary layer of the wing. It is a new solution for boundary layer control [7]. The DBD system does not have any moving parts such as rods, valves, diaphragms, cylinders or gears to activate it, thus creating no design problems that complicate the aircraft structure. One of the main mechanisms influencing the flow exerted by the DBD plasma actuator is the generation of “ion wind” [8,9]. As a consequence of flexible collisions between migrating charged particles and inert gas particles, they increase their energy, causing an “electric wind” that occurs in close proximity to the profile surface [10,11]. The construction of a plasma actuator is quite simple. It consists of two flat electrodes (the most commonly used metal/copper strips) that are separated by a dielectric. The dielectric prevents spark discharge that causes local increase in temperature. The first electrode is completely covered with a dielectric; the second electrode is directly exposed to the flowing air. Research by other scientists mainly focuses on changing the shape of solid copper electrodes into sawtooth, oval, rectangular and wave [12,13,14]. Changing the shape of the exposed electrode is aimed at increasing the discharge area [15,16]. These changes create a stronger “ion wind” affecting the air circulation in the boundary layer. The most frequently used frequency during experimental research is from several hundred Hz to several kHz [17,18,19,20]. The voltage range used during the experimental tests depends on the dielectric [21,22] used and ranges from a few kV to several dozen kV. The manuscript presents experimental studies of a plasma actuator with a new type of electrodes. Two mesh electrodes were used in the presented studies. The use of mesh electrodes in a plasma actuator is a new design solution. The presented tunnel tests of a plasma actuator with two mesh electrodes are a new solution, not described in the literature by other researchers. The most commonly used in experimental research are solid copper electrodes impermeable to air, [23,24,25,26,27,28,29]. In the presented experimental studies, the grounded electrode fully covered with a dielectric is much larger, it covers about 70% of the upper surface of the wing. The main purpose of the wind tunnel tests carried out to confirm the effectiveness of the new type of plasma actuator with two electrodes for controlling the boundary layer. The research was carried out for the wing model with the SD 7003 profile (made personally by the author of the manuscript) for an angle of attack of 15°; for such a high angle of attack, the profile loses lift under normal conditions. The critical angle of attack at which the SD 7003 profile has the maximum lift coefficient is about 11°.

2. Materials and Methods

Experimental research was carried out with the wing model with the SD 7003 profile, 250 mm wide and 250 mm long. The wing model is made of fiberglass, balsa and plywood. Two mesh electrodes are placed on the upper surface of the wing as shown in Figure 1. A large, grounded mesh electrode is 200 mm long and 200 mm wide is full covered with four layers of Kapton dielectric and is attached directly to the wing surface. The use of a dielectric to prevent spark discharges and high local temperature increase [30,31].
The use of mesh electrodes for the construction of a plasma actuator resulted from the previous experimental results of the author of the manuscript. Previous experimental research with plasma reactors with DBD discharges have shown that the use of mesh electrodes allows obtaining homogeneous discharges. The research carried out with DBD systems with small dimension mesh electrodes allowed for obtaining the highest efficiency of ozone generation during experimental research with plasma reactors. For the construction of plasma actuators, systems with the highest efficiency must be used, because the use of systems with low efficiency will increase the weight of the aircraft without the expected impact on the boundary layer.
The HV electrode is 200 mm long and 10 mm wide and is placed on the dielectric surface at a distance of 15 mm from the leading edge. Both mesh electrodes are made of AISI 304 stainless steel, it prevents oxidation of the electrode surface by ozone generated during DBD, the mesh size of the electrodes was 0.05 mm × 0.05 mm. The electrodes are connected to a high voltage power system with a value of several kV. The wing model was placed in the AeroLab wind tunnel (Aerolab LLC, Jessup, USA), which allows to control the air speed in the range of V = 4.5–65 m/s and measure the forces acting on the wing during experimental tests. The measuring stand and the wind tunnel are shown in Figure 2.
A typical DBD plasma actuator system with two solid electrodes is shown in Figure 3a. Figure 3b shows the setup and operation of the test system with two mesh electrodes.
Comparing the design of the plasma actuators in Figure 3a with classic plasma actuator with solid electrodes and Figure 3b with two mesh electrodes, differences in the structure and surface of the discharges can be seen. The use of mesh electrodes allows us to obtain a larger surface of discharges compared to the classic plasma actuator with solid electrodes; it is possible due to the use of an HV mesh electrode. Discharges in a plasma actuator with solid electrodes are generated at only one edge of the HV electrode. The use of mesh electrodes in the model presented in the manuscript allows for a larger area of discharges because the discharges occur at the two edges of the mesh electrode as well as directly through the surface of the HV electrode, which additionally increases the area of discharges. The entire surface of the high-voltage electrode forms one wide discharge.
Figure 4 compares the real design of the plasma actuator with solid electrodes in an asymmetric configuration Figure 4a and the tested plasma actuator with two mesh electrodes Figure 4b.
The experimental research presented in the manuscript were carried out for three air flow velocities of V = 5, 10 and 15 m/s and an angle of attack of 15°. During the experimental research, the air flow velocities were changed in steps of 5 m/s.
An autotransformer and a high voltage transformer 230/10,000 V 50 Hz were used to power the DBD plasma actuator located on the wing surface. Lissajous figures and high voltage were recorded during the experimental tests.
The measurements were performed with the Keysight DSO X 2012A 200 MHz, 2 GS/s oscilloscope (Keysight, Santa Rosa, CA, USA), equipped with a Tektronix P6015A high-voltage probe (Tektronix, Inc, Beaverton, OR, USA) and a Tektronix P2220 1:1/10:1 current probe (Tektronix, Inc, Beaverton, OR, USA). Figure 5 shows a diagram of the measurement system with individual elements marked. The internal structure of the wing model is also shown in Figure 5, and in particular the arrangement of the individual layers of the dielectric and electrodes. A photo of the real wing model used in the experimental tests is shown in Figure 1, with a description of the individual elements. The photo of the wing model shows a large, grounded electrode GND full covered with a dielectric; on the surface of the dielectric there is a high-voltage HV electrode.
During the experimental tests in the wind tunnel, photos of the wing model for individual air flow velocities were recorded using the Phantom V2511 (Vision Research, Wayne, NJ, USA) high-speed camera.
During the experimental research, the wing model was placed inside the AeroLab wind tunnel. The DBD plasma actuator is located on the upper surface of the wing model as shown in Figure 6. The wing model with the DBD plasma actuator was placed directly on the balancing force, which allows the registration of the forces acting on the model during experimental research. Figure 6 shows the wing model placed on the balancing force during experimental tests in the wind tunnel.
During the experimental research, a smoke generator was used, which allowed the observation of changes in air flow on the wing surface and the formation of turbulence.

3. Results

During the experimental research, use of the oscilloscope allowed for the recording of Lissajous figures with which the power of the discharges was calculated. Figure 7 shows an exemplary Lissajous figure for the discharge power of 1.0 W. The power of the discharges during the experimental research ranged of P = 1.0–2.2 W, with the supply voltage of Vp = 7.5–15 kV. High voltage power supply with a frequency of 50 Hz was used to power the DBD plasma actuator.
During the tunnel tests, the forces acting on the wing model were also recorded, as shown in Table 1.
The Table 1 compares the forces acting on the wing model under the same conditions with the plasma actuator turn on and turn off. The uncertainty of measurements, calculated on the basis of the results of experimental research, is presented in Table 2.
In addition to the results presented in Table 1, the effectiveness of the plasma actuator is also confirmed by photos taken with a high-speed camera. The use of a smoke generator and high-speed camera allows to observe the air flow for the system with the plasma actuator turn on and turn off. The photos show the influence of the DBD system on the change of air flow over the upper surface of the wing. Turning on the plasma actuator allows for a more laminar airflow as shown in Figure 8b. During the experiment, the camera recorded photos at 3000 frames per second, which provided high quality photos.
The presented results of experimental tests in the wind tunnel on the SD 7003 wing model show the effectiveness of the DBD plasma actuator with two mesh electrodes, which is confirmed by the results presented in Table 1 and the tunnel photos in Figure 8, Figure 9 and Figure 10. Experimental research were carried out for a high angle of attack for which the SD 7003 profile wing loses its lift under normal conditions (critical angle of attack about 11°).
Figure 8a shows the wing model with the plasma actuator turned off, with visible non-laminar airflow. The point of separation and turbulence are especially visible at the end of the wing near the trailing edge. Turning on the plasma actuator at the air velocity of V = 5 m/s in Figure 8b allowed to significantly reduce the turbulence that is visible in Figure 8a. The airflow in Figure 8b is not completely laminar but much less turbulent than the flow with the plasma actuator off Figure 8a. The tunnel photo shown in Figure 9a for an air velocity of 10 m/s and Figure 10a for an air velocity of 15 m/s for the configuration with plasma actuator turned off is non-laminar with visible turbulence, while in Figure 9b and Figure 10b with plasma actuator turned on, the airflow is more laminar at air flow velocity of V = 10 m/s and V = 15 m/s. Comparing Figure 8b, Figure 9b and Figure 10b (Plasma On), we can see the negative effect of airflow velocity on the efficiency of the plasma actuator. In Figure 9b and Figure 10b the air jets do not adhere to the wing, which results in a reduced increase in lift.
The lift coefficient CL was used to determine the lift force changes depending on the air flow velocity and the angle of attack. Figure 11 shows the change in the lift coefficient CL of the wing model with the plasma actuator turn off and turn on. The changes in the lift coefficient presented in Table 3 are most visible on the graph for the flow velocity in the range of V = 5–10 m/s, when the air flow velocity is low.
Figure 12 and Table 4 presents changes in resultant force depending on air flow velocity in the range of 5 to 15 m/s and angle of attack 15°.
The results of the experimental tests presented in Table 4 show the change of the resultant force trend for the air flow velocity in the range from V = 5 m/s to V = 15 m/s for the angle of attack of 15°.
The changes in the resultant force presented in the diagram in Figure 12 are small because the changes in the lift coefficient of the tested SD 7003 wing profile are small because the critical angle of attack for this profile is 11°. In the experimental tests, the experiment was carried out for an angle of 15° greater than the critical angle of attack. At an angle of attack greater than 11°, the SD 7003 profile loses total lift and stall occurs.
The use of a plasma actuator allowed to obtain a positive increase in the lifting force as well as the resultant force even in such unfavorable conditions.
The main factor influencing the increase in the lift force and the efficiency of the plasma actuator with two mesh electrodes is the increase in the discharge area. The discharge on the high-voltage mesh electrode is created over the entire surface of the electrode, creating a wide discharge belt (in a classic plasma actuator with a solid electrode, the discharge is generated only on one edge). The design solution presented in the manuscript is a new solution for changing the geometry of the electrodes and is not used by other researchers.
The experimental studies show that the efficiency of the plasma actuator depends on several factors, including air flow velocity V, as well as the parameters of the plasma actuator supply system and the power of the discharges. Many experimental studies confirm that the efficiency of DBD systems decreases with the increase in gas flow velocity (e.g., ozone generators, the concentration of ozone decreases) [32,33,34], the same is the case with DBD plasma actuators [35,36] because the operation of the plasma actuator is precisely to generate the plasma “ion wind”.

4. Conclusions

The results of the conducted experimental research confirm the effectiveness of the new type of plasma actuator with two mesh electrodes. Tunnel tests of the wing model with the SD7003 profile allowed to obtain an increase in the lift coefficient by 5% at a high angle of attack of 15° (critical angle of attack 11°), which is confirmed by Figure 11 and Table 3. The high efficiency of the tested design of the plasma actuator is possible because the discharges appear at both edges and directly through the surface of the high voltage electrode. These phenomena do not occur in the classic solution with impermeable solid electrodes, in which the discharges are only on one edge, discharges directly through the surface of the HV solid electrode are impossible. The geometry of the electrodes is a key factor in the efficiency of the plasma actuator. Increasing the discharge area allows for a higher gas ionization density, affecting the increase in the lift coefficient CL. Many researchers change the shape of the solid electrodes to increase the efficiency of the plasma actuator. The mesh electrode increases the effective surface of the discharges, thus increasing the efficiency of the plasma actuator with two mesh electrodes. Another important factor is the supply system, especially the supply voltage and frequency. Both of these factors directly affect the power of the discharges. The plasma actuator with two mesh electrodes described in the manuscript is a new design that requires further optimization.
The conducted experimental research and the obtained results show the potential of the new design of the plasma actuator. In order to determine the potential of the new design of the plasma actuator, it requires further experimental research to determine the optimal configuration of the system, one of the factors that should be examined is the determination of the mounting location and the number of HV electrodes.

Author Contributions

Conceptualization, E.G.; formal analysis, J.M.; investigation, E.G., J.P. and J.J.; project administration, J.L.; writing—original draft, E.G. All authors have read and agreed to the published version of the manuscript.

Funding

This research received no external funding.

Institutional Review Board Statement

Not applicable.

Informed Consent Statement

Not applicable.

Data Availability Statement

Data is contained within the article.

Acknowledgments

We would like to offer our sincere thanks to the Institute of Technical Sciences and Aviation, The State School of Higher Education Chełm (Poland) for agreeing to conduct tests in the wind tunnel.

Conflicts of Interest

The authors declare no conflict of interest.

References

  1. Xue, C.-J.; Han, Y.; Qi, W.-G.; Dai, J.-H. Landing-Gear Drop-Test Rig Development and Application for Light Airplanes. J. Aircr. 2012, 49, 2064–2076. [Google Scholar] [CrossRef]
  2. Pytka, J.; Budzyński, P.; Łyszczyk, T.; Józwik, J.; Michałowska, J.; Tofil, A.; Błażejczak, D.; Laskowski, J. Determining Wheel Forces and Moments on Aircraft Landing Gear with a Dynamometer Sensor. Sensors 2019, 20, 227. [Google Scholar] [CrossRef] [PubMed] [Green Version]
  3. Pytka, J.; Józwik, J.; Budzyński, P.; Łyszczyk, T.; Tofil, A.; Gnapowski, E.; Laskowski, J. Wheel Dynamometer System for Aircraft Landing Gear Testing. Measurement 2019, 148, 106918. [Google Scholar] [CrossRef]
  4. Zhou, Y.; Yunxia, C.; Rui, K. A Study of Aircraft Landing Gear Testing System on PHM. In Proceedings of the Prognostics and System Health Managment Conference, Montreal, QC, Canada, 25–29 September 2011; pp. 1–4. [Google Scholar] [CrossRef]
  5. Ninian, D.; Dakka, S.M. Design, Development and Testing of Shape Shifting Wing Model. Aerospace 2017, 4, 52. [Google Scholar] [CrossRef] [Green Version]
  6. Gerard, I.J. Mechanical Tests of Aircraft Structural Components. J. R. Aeronaut. Soc. 1932, 36, 673–703. [Google Scholar] [CrossRef]
  7. Gnapowski, E.; Pytka, J.; Jozwik, J.; Michalowska, J. Wind Tunnel Testing of Mesh Electrodes Plasma Actuator. In Proceedings of the 7th IEEE Workshop on Metrology for AeroSpace, Pisa, Italy, 22–24 June 2020; pp. 426–429. [Google Scholar]
  8. Whalley, R.D.; Choi, K.S. The Starting Vortex in Quiescent Air Induced by Dielectric-Barrier-Discharge Plasma. J. Fluid Mech. 2012, 703, 192–203. [Google Scholar] [CrossRef] [Green Version]
  9. Robinson, M. A History of the Electric Wind. Am. J. Phys. 1962, 30, 366–372. [Google Scholar] [CrossRef]
  10. Messanelli, F.; Belan, M. Ionic Wind Measurements on Multi-Tip Plasma Actuators. EPJ Web Conf. 2016, 114, 2073. [Google Scholar] [CrossRef] [Green Version]
  11. Séraudie, A.; Aubert, E.; Naudé, N.; Cambronne, J. Effect of Plasma Actuators on a Flat Plate Laminar Boundary Layer in Subsonic Conditions. In Proceedings of the 3rd AIAA Flow Control Conference, San Francisco, CA, USA, 5–8 June 2006. [Google Scholar]
  12. Wang, C.-C.; Durscher, R.; Roy, S. Three-Dimensional Effects of Curved Plasma Actuators in Quiescent Air. J. Appl. Phys. 2011, 109, 083305. [Google Scholar] [CrossRef] [Green Version]
  13. Roy, S.; Wang, C.C. Bulk Flow Modification with Horseshoe and Serpentine Plasma Actuators. J. Phys. D Appl. Phys. 2009, 42. [Google Scholar] [CrossRef]
  14. Berendt, A.; Podliński, J.; Mizeraczyk, J. Multi DBD Plasma Actuator for Flow Separation Control around NACA0012 and NACA0015 Airfoil Models. Przegląd Elektrotechniczny 2012, 88, 18–21. [Google Scholar]
  15. Leroy, P.; Audier, J.; Podlinski, A.; Berendt, D.H.; Mizeraczyk, J. Enhancement of Lift and Drag Performances of NACA0012 Airfoil by Multi-DBD Plasma Actuator with Additional Floating Interelectrodes. In Proceedings of the International Symposium on Electrohydrodynamics, Gdańsk, Poland, 23–26 September 2012. [Google Scholar]
  16. Gnapowski, E. Effect of Mesh Electrodes Geometry on the Ozone Concentration in the Presence of Micanite Dielectric. Adv. Sci. Technol. Res. J. 2018, 12, 76–80. [Google Scholar] [CrossRef]
  17. Kogelschatz, U.; Eliasson, B.; Egli, W. From Ozone Generators to at Television Screens: History and Future Potential of Dielectric-Barrier Discharges. Pure Appl. Chem. 1999, 71, 1819–1828. [Google Scholar] [CrossRef]
  18. Han, M.; Li, J.; Niu, Z.; Liang, H.; Zhao, G.; Hua, W.; Menghu, H.; Jun, L.; Zhongguo, N.; Hua, L.; et al. Aerodynamic performance enhancement of a flying wing using nanosecond pulsed DBD plasma actuator. Chin. J. Aeronaut. 2015, 28, 377–384. [Google Scholar] [CrossRef] [Green Version]
  19. Gnapowski, E.; Gnapowski, S.; Pytka, J. Effect of Mesh Geometry on Power, Efficiency, and Homogeneity of Barrier Discharges in the Presence of Glass Dielectric. IEEE Trans. Plasma Sci. 2018, 46, 3493–3498. [Google Scholar] [CrossRef]
  20. Deng, X.T.; Kong, M.G. Frequency Range of Stable Dielectric-Barrier Discharges in Atmospheric He and N2. IEEE Trans. Plasma Sci. 2004, 32, 1709–1715. [Google Scholar] [CrossRef]
  21. Gnapowski, E.; Gnapowski, S. Changes in the Power Discharge in a Plasma Reactor Using Porous Versus Solid Dielectric Barriers and Meshes Electrodes. IEEE Trans. Plasma Sci. 2016, 44, 1–5. [Google Scholar] [CrossRef]
  22. Kim, J.; Kim, S.-J.; Lee, Y.-N.; Kim, I.T.; Cho, G. Discharge Characteristics and Plasma Erosion of Various Dielectric Materials in the Dielectric Barrier Discharges. Appl. Sci. 2018, 8, 1294. [Google Scholar] [CrossRef] [Green Version]
  23. Asada, K.; Ninomiya, Y.; Fujii, K.; Oyama, A. Airfoil Flow Experiment on the Duty Cycle of DBD Plasma Actuator. In Proceedings of the 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition, Orlando, FL, USA, 5–8 January 2009. [Google Scholar]
  24. Zhao, G.; Li, Y.; Liang, H.; Han, M.; Wu, Y. Flow Separation Control on Swept Wing with Nanosecond Pulse Driven DBD Plasma Actuators. Chin. J. Aeronaut. 2015, 28, 368–376. [Google Scholar] [CrossRef] [Green Version]
  25. Patel, M.P.; Ng, T.T.; Vasudevan, S.; Corke, T.C.; Post, M.L.; McLaughlin, T.E.; Suchomel, C.F. Scaling Effects of an Aerodynamic Plasma Actuator. J. Aircr. 2008, 45, 223–236. [Google Scholar] [CrossRef] [Green Version]
  26. Qi, X.-H.; Yang, L.; Yan, H.-J.; Jin, Y.; Ren, C.-S. Plasma Actuator Performance Driven by Dual-Power Supply Voltage—AC High Voltage Superimposed with Pulse Bias Voltage. IEEE Trans. Plasma Sci. 2017, 45, 412–422. [Google Scholar] [CrossRef]
  27. Dong, D.; Hong, J.; Pouvesle, V.; Boucinha, W.R.; Leroy, A. Study of a DBD Plasma Actuator Dedicated to Airflow Separation Control. In Proceedings of the IEEE 35th International Conference on Plasma Science, Karlsruhe, Germany, 15–19 June 2008; p. 1. [Google Scholar]
  28. Huang, J.; Corke, T.C.; Thomas, F.O. Plasma Actuators for Separation Control of Low-Pressure Turbine Blades. AIAA J. 2012; 44, 51–57. [Google Scholar]
  29. Nishida, H.; Shiraishi, T. Experimental Characterization of Dual-Grounded Tri-Electrode Plasma Actuator. AIAA J. 2015, 53, 3157–3166. [Google Scholar] [CrossRef]
  30. Gnapowski, E.; Gnapowski, S.; Pytka, J. The Impact of Dielectrics on the Electrical Capacity, Concentration, Efficiency Ozone Generation for the Plasma Reactor with Mesh Electrodes. Plasma Sci. Technol. 2018, 20, 085505. [Google Scholar] [CrossRef] [Green Version]
  31. Jiang, L.; Li, Q.; Zhu, D.; Attoui, M.; Deng, Z.; Tang, J.; Jiang, J. Comparison of Nanoparticle Generation by Two Plasma Techniques: Dielectric Barrier Discharge and Spark Discharge. Aerosol Sci. Technol. 2017, 51, 206–213. [Google Scholar] [CrossRef] [Green Version]
  32. Cuong, L.C.; Nghi, N.H.; Dieu, T.V.; Oanh, D.T.Y.; Vuong, D.D. Influence of Oxygen Concentration, Feed Gas Flow Rate and Air Humidity on the Output of Ozone Produced by Corona Discharge. Vietnam. J. Chem. 2019, 57, 604–608. [Google Scholar] [CrossRef]
  33. Vaduganathan, L.; Poonamallie, B.A.; Nagalingam, M. Effects of Temperature and Flow Rates of Ozone Generator on the DBD by Varying Various Electrical Parameters. Am. J. Appl. Sci. 2012, 9, 1496–1502. [Google Scholar] [CrossRef] [Green Version]
  34. Prasetyaningrum, A.; Kusumaningtyas, D.A.; Suseno, P.; Ratnawati, R. Effect of pH and Gas Flow Rate on Ozone Mass Transfer of Κ-Carrageenan Solution in Bubble Column Reactor. Reakt. Chem. Eng. J. 2018, 18, 177–182. [Google Scholar] [CrossRef]
  35. Shimizu, K.; Mizuno, Y.; Blajan, M. Basic Study on Flow Control by Using Plasma Actuator. IEEE Ind. Appl. Soc. Annu. Meet. 2013, 51, 1–6. [Google Scholar] [CrossRef]
  36. Vorobiev, A.; Rennie, R.M.; Jumper, E.J. Lift Enhancement by Plasma Actuators at Low Reynolds Numbers. J. Aircr. 2013, 50, 12–19. [Google Scholar] [CrossRef]
Sensors 21 00363 g001 550
Figure 1. Wing model with the profile SD7003, with a visible plasma actuator with two mesh electrodes.
Figure 1. Wing model with the profile SD7003, with a visible plasma actuator with two mesh electrodes.
Sensors 21 00363 g001
Sensors 21 00363 g002 550
Figure 2. Measurement stand with equipment.
Figure 2. Measurement stand with equipment.
Sensors 21 00363 g002
Sensors 21 00363 g003 550
Figure 3. Construction of plasma actuators: (a) classic plasma actuator with solid electrodes with visible discharges only on one edge, (b) plasma actuator with two mesh electrodes with discharges visible on two edges and directly through the surface of the HV electrode.
Figure 3. Construction of plasma actuators: (a) classic plasma actuator with solid electrodes with visible discharges only on one edge, (b) plasma actuator with two mesh electrodes with discharges visible on two edges and directly through the surface of the HV electrode.
Sensors 21 00363 g003
Sensors 21 00363 g004 550
Figure 4. Comparison of the design of plasma actuators: (a) classic with solid electrodes and, (b) with two mesh electrodes.
Figure 4. Comparison of the design of plasma actuators: (a) classic with solid electrodes and, (b) with two mesh electrodes.
Sensors 21 00363 g004
Sensors 21 00363 g005 550
Figure 5. Measurement diagram and electrode system arranged on the wing model.
Figure 5. Measurement diagram and electrode system arranged on the wing model.
Sensors 21 00363 g005
Sensors 21 00363 g006 550
Figure 6. Wing model placed inside the wind tunnel.
Figure 6. Wing model placed inside the wind tunnel.
Sensors 21 00363 g006
Sensors 21 00363 g007 550
Figure 7. Lissajous figure for P = 1.0 W discharge power, at Vp = 7.5 kV supply voltage.
Figure 7. Lissajous figure for P = 1.0 W discharge power, at Vp = 7.5 kV supply voltage.
Sensors 21 00363 g007
Sensors 21 00363 g008 550
Figure 8. Tunnel photos of the wing model with the SD 7003 profile for the angle of attack α = 15° at the air flow velocity V = 5 m/s for; (a) plasma actuator turned off and (b) plasma actuator turned on.
Figure 8. Tunnel photos of the wing model with the SD 7003 profile for the angle of attack α = 15° at the air flow velocity V = 5 m/s for; (a) plasma actuator turned off and (b) plasma actuator turned on.
Sensors 21 00363 g008
Sensors 21 00363 g009 550
Figure 9. Tunnel photos of the wing model with the SD 7003 profile for the angle of attack α = 15° at the air flow velocity V = 10 m/s for; (a) plasma actuator turned off and (b) plasma actuator turned on.
Figure 9. Tunnel photos of the wing model with the SD 7003 profile for the angle of attack α = 15° at the air flow velocity V = 10 m/s for; (a) plasma actuator turned off and (b) plasma actuator turned on.
Sensors 21 00363 g009
Sensors 21 00363 g010 550
Figure 10. Tunnel photos of the wing model with the SD 7003 profile for the angle of attack α = 15° at the air flow velocity V = 15 m/s for; (a) plasma actuator turned off and (b) plasma actuator turned on.
Figure 10. Tunnel photos of the wing model with the SD 7003 profile for the angle of attack α = 15° at the air flow velocity V = 15 m/s for; (a) plasma actuator turned off and (b) plasma actuator turned on.
Sensors 21 00363 g010
Sensors 21 00363 g011 550
Figure 11. Graph of changes in the trend of the lift force coefficient for the wing model for the angle of attack α = 15° and the air flow speed in the range of V = 5–15 m/s, when the plasma actuator turn on and turn off.
Figure 11. Graph of changes in the trend of the lift force coefficient for the wing model for the angle of attack α = 15° and the air flow speed in the range of V = 5–15 m/s, when the plasma actuator turn on and turn off.
Sensors 21 00363 g011
Sensors 21 00363 g012 550
Figure 12. Changes in the resultant force trend depending on air flow velocity in the range of 5–15 m/s and angle of attack 15°.
Figure 12. Changes in the resultant force trend depending on air flow velocity in the range of 5–15 m/s and angle of attack 15°.
Sensors 21 00363 g012
Table
Table 1. Normal and axial force measurements at angle of attack of 15°.
Table 1. Normal and axial force measurements at angle of attack of 15°.
V (m/s)Normal Force (N)Axial Force (N)
Plasma actuator
OFFONOFFON
51.521.570.080.09
106.466.460.310.31
1513.3513.480.650.66
Table
Table 2. The uncertainty measured of forces for angle of attack of 15°.
Table 2. The uncertainty measured of forces for angle of attack of 15°.
Measurement Uncertainty
Normal Force (N)Axial Force (N)
Plasma actuator
V (m/s)OFFONOFFON
50.0070.0130.0020.006
100.0030.0070.0020.006
150.0830.0750.0040.008
Table
Table 3. Change of the lift coefficient CL for the angle of attack of 15°.
Table 3. Change of the lift coefficient CL for the angle of attack of 15°.
V (m/s)Lift Coefficient CL
Plasma actuator OFFPlasma actuator ON
51.571.62
101.611.62
153.423.44
Table
Table 4. Changes in resultant force depending on air flow velocity and angle of attack 15°.
Table 4. Changes in resultant force depending on air flow velocity and angle of attack 15°.
V (m/s)Resultant Force (N)
Plasma actuator OFFPlasma actuator ON
50.50.53
101.982
154.194.25
Publisher’s Note: MDPI stays neutral with regard to jurisdictional claims in published maps and institutional affiliations.

Share and Cite

MDPI and ACS Style

Gnapowski, E.; Pytka, J.; Józwik, J.; Laskowski, J.; Michałowska, J. Wind Tunnel Testing of Plasma Actuator with Two Mesh Electrodes to Boundary Layer Control at High Angle of Attack. Sensors 2021, 21, 363. https://doi.org/10.3390/s21020363

AMA Style

Gnapowski E, Pytka J, Józwik J, Laskowski J, Michałowska J. Wind Tunnel Testing of Plasma Actuator with Two Mesh Electrodes to Boundary Layer Control at High Angle of Attack. Sensors. 2021; 21(2):363. https://doi.org/10.3390/s21020363

Chicago/Turabian Style

Gnapowski, Ernest, Jarosław Pytka, Jerzy Józwik, Jan Laskowski, and Joanna Michałowska. 2021. "Wind Tunnel Testing of Plasma Actuator with Two Mesh Electrodes to Boundary Layer Control at High Angle of Attack" Sensors 21, no. 2: 363. https://doi.org/10.3390/s21020363

APA Style

Gnapowski, E., Pytka, J., Józwik, J., Laskowski, J., & Michałowska, J. (2021). Wind Tunnel Testing of Plasma Actuator with Two Mesh Electrodes to Boundary Layer Control at High Angle of Attack. Sensors, 21(2), 363. https://doi.org/10.3390/s21020363

Note that from the first issue of 2016, this journal uses article numbers instead of page numbers. See further details here.

Article Metrics

Back to TopTop