Articles de revues : « Aerodynamic of plasmas »

1

Caruana, D. « Plasmas for aerodynamic control ». Plasma Physics and Controlled Fusion 52, n^o 12 (15 novembre 2010) : 124045. http://dx.doi.org/10.1088/0741-3335/52/12/124045.

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Aleshin, B. S., V. Yu Khomich et S. L. Chernyshev. « DEVELOPMENT TRENDS IN PLASMA AERODYNAMICS ». Доклады Российской академии наук. Физика, технические науки 508, n^o 1 (1 janvier 2023) : 3–8. http://dx.doi.org/10.31857/s2686740023010017.

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The most promising areas of research in the field of plasma aerodynamics are proposed. On the basis of the presented experimental data obtained recently, the possibilities of using the volumetric force effect on the gas flow in aerodynamic applications, which is realized with the help of near-surface electric discharges, are considered. One of these applications is to increase the length of the laminar section of the boundary layer on the swept wing in order to reduce the aerodynamic drag of the aircraft in the cruise flight mode. The second direction is associated with the control of the three-dimensional separation of the boundary layer on the elements of the mechanization of the swept wing in the take-off and landing modes. And the third direction is the reduction of surface friction in the turbulent boundary layer, which is realized on most of the surface of modern near- and supersonic aircraft. The proposed studies are not only of applied, but also of fundamental importance due to the physical complexity of the studied phenomena.

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Omidi, Javad. « Advances and opportunities in wind energy harvesting using plasma actuators : a review ». Clean Energy 8, n^o 1 (19 janvier 2024) : 197–225. http://dx.doi.org/10.1093/ce/zkad085.

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Abstract The dielectric barrier discharge plasma actuator has been recognized as a leading technology for controlling fluid flow and has found remarkable applications in wind energy harvesting over the past decade. Wind turbine aerodynamics are critical in this concept and performance is mainly determined by flow controllers, although significant technical progress is still required. This paper examines all the critical studies to investigate the potential application of plasma actuators for airflow control over wind turbines. This approach has been divided into three categories: wind turbine airfoils, horizontal-axis wind turbines and vertical-axis wind turbines aerodynamic performance and generated power. Finally, the potential functions of plasma actuators in current and future wind turbine generators are discussed. These actuators offer promising solutions to increasing power output, minimizing torque fluctuations and enabling self-starting capabilities, particularly in vertical-axis wind turbines. By adjusting blade pitch angles in conjunction with plasma actuators, significant improvements in airflow optimization and power extraction have been demonstrated. Despite the advancements, challenges persist, such as determining optimal actuator placement and overcoming structural limitations, especially concerning 3D effects and high Reynolds numbers. While plasma actuators enhance aerodynamic efficiency, their complexity needs to be balanced against marginal gains in power production, especially in high-megawatt turbines, for which controlling flow at low wind speeds is challenging. Future research must focus on the sustainable integration of plasma actuators, pitch angle adjustments and active control mechanisms to fully exploit the potential of wind energy for a sustainable future.

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Aleksandrov, N. L., S. V. Kindysheva et I. V. Kochetov. « Kinetics of low-temperature plasmas for plasma-assisted combustion and aerodynamics ». Plasma Sources Science and Technology 23, n^o 1 (4 février 2014) : 015017. http://dx.doi.org/10.1088/0963-0252/23/1/015017.

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Bletzinger, P., B. N. Ganguly, D. Van Wie et A. Garscadden. « Plasmas in high speed aerodynamics ». Journal of Physics D : Applied Physics 38, n^o 4 (4 février 2005) : R33—R57. http://dx.doi.org/10.1088/0022-3727/38/4/r01.

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Xin, Wang, Yan Jie et Zhang Yerong. « Exploring research on high-speed vehicle attitude control with plasma virtual flap manipulation ». Proceedings of the Institution of Mechanical Engineers, Part G : Journal of Aerospace Engineering 233, n^o 10 (9 octobre 2018) : 3627–34. http://dx.doi.org/10.1177/0954410018804089.

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This work provides an attitude solution for a high-speed vehicle using plasma aerodynamic control called “plasma virtual flap” manipulation. This paper describes the concept of using plasma active control as plasma virtual flap for off-design attitude manipulation problem. Design of an attitude controller considering plasma aerodynamic effects for the high-speed vehicle is presented. The aerodynamic lift and drag force features in the high speed, long duration cruise flight with plasma actuator effect are introduced, where the estimated models and attitude controller are established. This paper documents the development and capabilities of plasma virtual flap attitude control authority. Simulation results are presented to exhibit the effectiveness of the proposed method.

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Aleshin, B. S., V. Yu Khomich et S. L. Chernyshev. « Development Trends in Plasma Aerodynamics ». Doklady Physics 68, n^o 1 (janvier 2023) : 1–5. http://dx.doi.org/10.1134/s1028335823010019.

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Hui, Zheng, Xingjun Hu, Peng Guo, Zewei Wang et Jingyu Wang. « Separation Flow Control of a Generic Ground Vehicle Using an SDBD Plasma Actuator ». Energies 12, n^o 20 (9 octobre 2019) : 3805. http://dx.doi.org/10.3390/en12203805.

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Quiescent flow and wind tunnel tests were performed to gain additional physical insights into flow control for automotive aerodynamics using surface dielectric barrier discharge plasma actuators. First, the aerodynamic characteristics of ionic wind were studied, and a maximum induced velocity of 3.3 m/s was achieved at an excitation voltage of 17 kV. Then, the optimal installation position of the actuator and the influence of the excitation voltage on flow control at different wind speeds were studied. The conclusions drawn are as follows. The effect of flow control is better when the upper electrode of the actuator is placed at the end of the top surface, increasing the likelihood of the plasma generation region approaching the natural separation location. The pressure on top of the slanted surface is primarily affected by airflow acceleration at a low excitation voltage and by the decrease of the separation zone at a high excitation voltage. The maximum drag reduction can be realized when the maximum velocity of ionic wind reaches 1.71 m/s at a wind speed of 10 m/s and 2.54 m/s at a wind speed of 15 m/s. Moreover, effective drag reduction can be achieved only by continuing to optimize the actuator to generate considerable thrust at a high wind speed.

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Tomohisa, Ohtake, Muramatsu Akinori, Motohashi Tatsuo et Kobayashi Shunsaku. « 1199 IMPROVEMENT OF AERODYNAMIC CHARACTERISTICS OF A NACA0012 AIRFOIL APPLIED A DBD PLASMA ACTUATOR IN LOW REYNOLDS NUMBERS ». Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2013.4 (2013) : _1199–1_—_1199–6_. http://dx.doi.org/10.1299/jsmeicjwsf.2013.4._1199-1_.

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Barni, Ruggero, Hector Eduardo Roman et Claudia Riccardi. « Ionizing Waves in Surface Dielectric Barrier Discharges Plasma Actuators ». Actuators 13, n^o 3 (22 février 2024) : 86. http://dx.doi.org/10.3390/act13030086.

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Plasma actuators have been proposed as a tool to produce hydrodynamical effects in the boundary layer of aerodynamical flows. We have analyzed some properties of these systems using suitable plasma diagnostics based on the emissivity characteristics of such plasmas. The direction and the velocity of propagation of the ionizing wave spreading on the dielectric surface were measured (in the 100–200 km/s range), and it was demonstrated that it behaves like a cathode-directed streamer. The averaged electron temperature (4–5 eV) and the reduced field strength (E/N ≈ 6 × 1019 V·m2) of the ionizing wave switching the discharges on were measured, too.

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Parent, Bernard, Mikhail N. Shneider et Sergey O. Macheret. « Detailed Modeling of Plasmas for Computational Aerodynamics ». AIAA Journal 54, n^o 3 (mars 2016) : 898–911. http://dx.doi.org/10.2514/1.j054624.

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Yue Taipeng, 岳太鹏, 李应红 Li Yinghong, 张建邦 Zhang Jianbang et 崔巍 Cui Wei. « Airflow characteristic of multiphase plasma aerodynamic actuation ». High Power Laser and Particle Beams 23, n^o 4 (2011) : 985–90. http://dx.doi.org/10.3788/hplpb20112304.0985.

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Patel, Mehul P., T. Terry Ng, Srikanth Vasudevan, Thomas C. Corke, Martiqua L. Post, Thomas E. McLaughlin et Charles F. Suchomel. « Scaling Effects of an Aerodynamic Plasma Actuator ». Journal of Aircraft 45, n^o 1 (janvier 2008) : 223–36. http://dx.doi.org/10.2514/1.31830.

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IIDA, Akiyoshi, et Hiroshi Yokoyama. « 1109 Aerodynamic Noise Control with Plasma Actuators ». Proceedings of the Fluids engineering conference 2013 (2013) : _1109–01_—_1109–02_. http://dx.doi.org/10.1299/jsmefed.2013._1109-01_.

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Cheng Yu-Feng, Nie Wan-Sheng et Li Guo-Qiang. « Numerical study of plasma aerodynamic actuation mechanism ». Acta Physica Sinica 61, n^o 6 (2012) : 060509. http://dx.doi.org/10.7498/aps.61.060509.

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Yang, Bo, Hesen Yang, Ning Zhao, Hua Liang, Zhi Su et Dongsheng Zhang. « Experimental Study on Hypersonic Double-Wedge Induced Flow Based on Plasma Active Actuation Array ». Aerospace 11, n^o 1 (9 janvier 2024) : 60. http://dx.doi.org/10.3390/aerospace11010060.

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The double-wedge configuration is a typical characteristic shape of the rudder surface of high-speed aircraft. The impact of the shock wave/boundary layer interaction and the shock wave/shock wave interaction resulting from the double wedge on aircraft aerodynamics cannot be ignored. The aerodynamic performance of the aircraft would be seriously affected. Accordingly, to reduce the wave drag, and to relieve the thermal load and pressure load, flow control is required for the shock wave/shock wave interaction and the shock wave/boundary layer interaction induced by the double-wedge configuration. In this paper, double-wedge shock wave/shock wave interaction is controlled by a high-energy surface arc discharge array and observed by high-speed schlieren flow field measurement at Mach 8. The 30-channel discharge array is set on the primary wedge plane, and actuation is generated. Hypersonic V shock wave/shock wave interaction is effectively controlled by the shock wave array induced by the high-energy surface arc discharge array, which makes the shock wave/shock wave interaction structure disappear or intermittent. The potential control mechanism is to reduce strong shock wave interaction by transforming the type of shock wave interaction. Therefore, the ability of plasma array actuation to control complex shock wave/shock wave interaction is verified, which provides a new method for hypersonic shock wave/shock wave interaction control.

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Enjieu Kadji, H. G., et B. R. Nana Nbendjo. « Passive aerodynamics control of plasma instabilities ». Communications in Nonlinear Science and Numerical Simulation 17, n^o 4 (avril 2012) : 1779–94. http://dx.doi.org/10.1016/j.cnsns.2011.09.017.

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Kong, Weihong, Keyi Guo et You Li. « Study on the Active Control of the Dynamic Stall of Rotor Airfoils Based on Plasma Excitation ». Aerospace 11, n^o 6 (15 juin 2024) : 474. http://dx.doi.org/10.3390/aerospace11060474.

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This paper studies a rotor dynamic stall control method using an alternating current dielectric barrier discharge (AC DBD) plasma actuator through numerical simulation methods. The flow field evolution during a dynamic stalling process under the excitation of AC DBD plasma discharge is analyzed using the two-dimensional Reynolds time-averaged (RANS) method. The impact of the AC DBD plasma discharge on the flow field is then simulated using the phenomenological method. The influence of the position and intensity of the plasma excitation on the static stall characteristics of the NACA0012 airfoil is also studied. Deformed mesh and dynamic mesh techniques are used to simulate an aerodynamic environment with variable incoming flow and variable angles of attraction on a rotor airfoil. The application of AC DBD plasma excitation for controlling mild and deep dynamic stalls of rotor blades is investigated. The obtained results show that the AC DBD plasma excitation accelerated the evolution and shedding of dynamic stall vortices and facilitated the reattachment of airflow. The application of plasma excitation allowed for significantly increasing the static stall angle of the airfoil and improving the lift coefficient. In addition, the intensity of the plasma excitation is a key factor affecting the control. Moreover, the application of AC DBD plasma excitation for rotor dynamic stalls allowed for reducing the size of the dynamic stall vortex, which helped mitigate the aerodynamic hysteresis effect caused by the dynamic stall and accelerated the recovery from aerodynamic forces.

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Niu, Zhong-Guo, Xiang-Hui Xu, Jian-Feng Wang, Jia-Li Jiang et Hua Liang. « Experiment on longitudinal aerodynamic characteristics of flying wing model with plasma flow control ». Acta Physica Sinica 71, n^o 2 (2022) : 024702. http://dx.doi.org/10.7498/aps.71.20211425.

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Horizontal tail is eliminated from the flying wing layout for improving the low observable and aerodynamic efficiency, resulting in degrading longitudinal maneuverability and fight stability. The low speed wind tunnel test study of improving the longitudinal aerodynamic characteristics of large aspect ratio flying wing model is carried out by using plasma flow control technology. The flying wing model has a leading-edge sweep angle of 34.5° and an aspect ratio of 5.79. The reasons for deteriorating the static maneuverability and stability of the flying wing model and the mechanism of plasma control of the flow field and longitudinal aerodynamic characteristics are studied by particle image velocimetry (PIV) flow visualization and static force measurement test. The control law of plasma control of the flight maneuverability and stability of the flying wing model is studied through flight test. The fact that the flow separation of the outer wing of the flying wing model occurs earlier than the inner wing and the wing is swept back can result in the forward movement of the aerodynamic center and the deterioration of the longitudinal static stability. The shock disturbance induced by plasma can suppress the flow separation of the suction surface, thereby extending the linear section of the lift curve of the model, preventing the aerodynamic center from moving forward, and improving the longitudinal static stability. When the wind speed is 50 m/s, the plasma control improves the horizontal rudder efficiency at a high angle of attack of the flying wing model, increases the maximum lift coefficient of the model by about 0.1, and postpones the stall angle of attack by more than 4° at different rudder angles. The plasma control allows the flying model to follow the command movement better while flying, increases the flying pitch limit angle from 11.5° to 15.1°, reduces the amplitude of longitudinal disturbance motion by 2°, and reduces the oscillation attenuation time from 15 to 8 s, thereby improving the longitudinal flight maneuverability and stability of the flying wing model. It can be seen that plasma flow control technology has great potential applications in improving the flight quality of flying wing layout.

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Jia, Min, Yinxiang Zang, Wei Cui, Dong Lin, Zhibo Zhang et Huimin Song. « Experimental Investigation on Flow Characteristics and Ignition Performance of Plasma-Actuated Flame Holder ». Processes 10, n^o 9 (14 septembre 2022) : 1848. http://dx.doi.org/10.3390/pr10091848.

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Improving the performance of flame holders has been a key focus of research on ramjet combustors. The plasma actuator has the potential to improve the ignition performance by manipulating the flow field of the flame holder. In this study, a plasma-actuated flame holder was designed. The aim of this study is to improve the performance of ramjet combustor by applying plasma discharge to the flame holder. The aerodynamic effects and ignition performance of the flame holder were investigated. The results demonstrated that the induced jet direction of the surface arc discharge was perpendicular to the actuator. The induced jet dissipated faster at lower pressures. The aerodynamic actuation intensity and jet area increased with the number of channels of surface arc discharges. Increasing discharge frequencies can increase the discharge times and jet height. The aerodynamic effects under a microsecond pulse duration were better than those under a nanosecond pulse duration. Actuators installed on the inside surface showed better performance than those installed outside. Under different total flow temperature conditions, the plasma-actuated flame holder significantly extended the ignition pressure limit and increased the combustion efficiency by 9.12% and 4.3% on average, respectively.

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Gulec, A., L. Oksuz et N. Hershkowitz. « Optical studies of dielectric barrier plasma aerodynamic actuators ». Plasma Sources Science and Technology 20, n^o 4 (7 juillet 2011) : 045019. http://dx.doi.org/10.1088/0963-0252/20/4/045019.

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Bénard, Nicolas, Jérôme Jolibois, Eric Moreau, Roberto Sosa, Guillermo Artana et Gérard Touchard. « Aerodynamic plasma actuators : A directional micro-jet device ». Thin Solid Films 516, n^o 19 (août 2008) : 6660–67. http://dx.doi.org/10.1016/j.tsf.2007.11.039.

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Wu, Yun, Ying-Hong Li, Min Jia, Hua Liang et Hui-Min Song. « Experimental investigation of nanosecond discharge plasma aerodynamic actuation ». Chinese Physics B 21, n^o 4 (avril 2012) : 045202. http://dx.doi.org/10.1088/1674-1056/21/4/045202.

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Moreau, Eric, Christophe Louste, Guillermo Artana, Maxime Forte et Gérard Touchard. « Contribution of Plasma Control Technology for Aerodynamic Applications ». Plasma Processes and Polymers 3, n^o 9 (17 novembre 2006) : 697–707. http://dx.doi.org/10.1002/ppap.200600059.

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Li, Ang, Hongjiang Cui, Ying Guan, Jichen Deng, Ying Zhang et Wu Deng. « Study on Aerodynamic Drag Reduction by Plasma Jets for 600 km/h Vacuum Tube Train Sets ». Machines 11, n^o 12 (8 décembre 2023) : 1078. http://dx.doi.org/10.3390/machines11121078.

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In order to break through the speed bottleneck, researchers envision using tubes to cover high-speed maglev trains and extract some of the air inside the tubes, creating a low-density environment on the ground, greatly reducing the aerodynamic drag of the trains, and in a relatively economical and feasible way, making high subsonic (600 km/h and above) and even supersonic ground transportation possible. The faster the running speed of high-speed trains, the greater the impact of aerodynamic drag on their energy consumption. Studying the aerodynamic characteristics of trains with a speed of 600 km/h can help optimize the aerodynamic shape of the train, reduce aerodynamic drag, and reduce energy consumption. This has positive implications for improving train energy efficiency, reducing energy consumption, and environmental impact. This paper adopts the numerical simulation method to study the drag reduction effect of the plasma arrangement and different excitation speeds on the train set in four positions when the incoming wind speed is 600 km/h, to analyze the mechanism of drag reduction, and then to analyze the combination of working conditions in order to investigate the drag reduction effect of plasma on the vacuum tube train set with an ambient pressure of 10,000 Pa. The findings demonstrate that the plasma induces the directional flow of the gas close to the wall to move the flow separation point backward and delay the separation of the flow, thereby reducing the front and rear differential pressure drag of the train set and lowering the aerodynamic drag coefficient of the entire train. The plasma arrangement is located at the rear of the flow separation point and in close proximity to the flow separation point. The pneumatic drag reduction effect peaks when the excitation speed reaches 0.2 times the train speed and the pneumatic drag reduction ratio is around 0.88%; the pneumatic drag reduction ratio of the rear car peaks when the excitation speed reaches 0.25 times the train speed and the pneumatic drag reduction ratio is 1.62%. The SDBD (Surface Dielectric Barrier Discharge) device is installed at the flow separation point around the nose tip of the rear car.

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Wang, Chin-Cheng, et Ching-Po Wen. « Aerodynamic drag reduction for a truck model using DBD plasma actuators ». Advances in Mechanical Engineering 14, n^o 3 (mars 2022) : 168781322210878. http://dx.doi.org/10.1177/16878132221087852.

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In this study, the effect of DBD plasma actuator based active flow control for a truck model was investigated. Two different electrode shapes which are linear and comb-shaped plasma actuators, are considered. The two DBD plasma actuators are placed at the leading edge or the trailing edge of the trailer, respectively. First, the drag reduction for the DBD plasma actuators at input voltages varying from 6 to 14 kVpp are compared. At a Reynolds number of 25,000, the maximum drag reduction using three comb-shaped plasma actuators at the trailing edge of the trailer is 8.7%, while the maximum drag reduction of three linear plasma actuators is approximately 6%. Then flow visualization behind the truck is performed. At a Reynolds number of 3500 and an input voltage of 14 kVpp, the results show that three comb-shaped plasma actuators installed at the trailing edge of the trailer produce a significant reduction in the wake region. In addition, the PIV measurement is used to quantize the flow field. It is observed that comb-shaped plasma actuators change the slope of the wake region more significantly than using linear plasma actuators. Therefore, this study shows that the use of DBD plasma actuators qualitatively and quantitatively reduces aerodynamic drag.

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Rashid, Shagufta, Fahad Nawaz, Adnan Maqsood, Shuaib Salamat, Rizwan Riaz, Laurent Dala et Riaz Ahmad. « Modeling and Analysis of Shock Reduction through Counterflow Plasma Jets ». Mathematical Problems in Engineering 2021 (14 juin 2021) : 1–17. http://dx.doi.org/10.1155/2021/5592855.

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The study presents a numerical investigation of aerodynamic drag reduction by implementing a counterflow plasma jet, emanating from the stagnation point of an aerodynamic surface in a supersonic regime with a constant pressure ratio PR = 3 , and compares findings with a conventional opposing jet. The computational study is carried out by solving three-dimensional and axisymmetric Navier–Stokes equations for counterflow plasma-jet interaction. The calculations are performed at free-stream Mach ( M ∞ = 1.4) with sea level stagnation conditions. The weakly ionized argon plasma jet generated by a plasma torch has constant stagnation pressure and temperature of 303,975 Pa and 3000 K . The effect of the Mach number and the angle of attack variation on plasma-jet effectiveness is also analyzed. The results indicate that the counterflow plasma jet reduces more drag (in twice) compared to the conventional jet (nonplasma). The gravitational, magnetic field effect and chemical processes in the plasma formation are considered negligible. It is inferred that the effectiveness of the counterflow plasma jet strongly depends upon the jet stagnation temperature.

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Ghosh, Aniruddha, Shailendra Bhatia et Somnath Chattopadhyaya. « Prediction of Heat Distribution Shape and Nozzle Diameter of Plasma Arc Cutter ». Advanced Materials Research 284-286 (juillet 2011) : 2465–68. http://dx.doi.org/10.4028/www.scientific.net/amr.284-286.2465.

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Theoretical three-dimensional Gaussian heat distribution model of the complex heat flow and plasma properties of cutting plasma torches have been developed. For cutting metallic plates, plasma torches must produce a narrow supersonic plasma jet with enough energy and momentum densities to melt, vaporize, and remove the metal from the impingement region. Our model allows us to study the details of the heat distribution and to make predictions on pick temperature development on metal surface, heat transfer to the work piece, force i.e. the forces acting on the melt (aerodynamic drag, gravity, viscosity and surface tension) during plasma arc cutting, the main forces acting on the melt is believed to be the aerodynamic drag force and the gravity is significant only for thick metal plates. With the help of these assumptions and diameter of Gaussian heat source’s volume, diameter of nozzle has been calculated for thin work piece. A good agreement is found between the model results and the available experimental data.

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Sun, Jie, Fuxing Zhang, Jin Wang, Jakov Baleta, Gongnan Xie et Bengt Sunden. « Effect of dielectric barrier discharge plasma on film cooling performance ». Thermal Science 26, n^o 5 Part B (2022) : 4157–68. http://dx.doi.org/10.2298/tsci2205157s.

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To improve film cooling effectiveness of a gas turbine blade, a kind of plasma actuator is introduced on the blade surface. The effect of three arrangements of plasma actuators on flow characteristics and film cooling performance is numerically investigated by a verified turbulence model. Results show that the coolant air under plasma is pulled down to the wall, and the near-wall air is sped up to promote the film cooling effectiveness downstream the wall. It is discovered that the plasma actuators near the film hole show weaker aerodynamic actuation than that downstream the wall. Compared with the plasma actuators off case, the maximum improvement in the wall-averaged film cooling effectiveness of the case with up plasma actuators is 11.7% under low blowing ratios. The wall-averaged film cooling effectivenesses of the cases with down plasma actuators and up-down plasma actuators increase by 138.3% and 122.9% under the blowing ratio of 1.5.. Vortex structures are broken up, and vortex is separated by two jets induced by aerodynamic actuation. The maximum wall pressure difference reaches 1.89% when plasma actuator is arranged downstream the wall.

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Golub, V. V., A. S. Saveliev, V. A. Sechenov, E. E. Son et D. V. Tereshonok. « Plasma aerodynamics in a supersonic gas flow ». High Temperature 48, n^o 6 (décembre 2010) : 903–9. http://dx.doi.org/10.1134/s0018151x10060180.

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Sun, Min, Bo Yang, Jian Min Li et Ming Kai Lei. « Experimental Investigation on Stall Separation Control on NACA0015 Airfoil by Steady Plasma Aerodynamic Actuation ». Advanced Materials Research 516-517 (mai 2012) : 726–30. http://dx.doi.org/10.4028/www.scientific.net/amr.516-517.726.

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Experimental investigation was performed to study the influence law of the free-stream speed, angle of attack and actuation voltage on the control effectiveness of NACA0015 airfoil stall separation suppression by steady plasma aerodynamic actuation. It is found that plasma actuation can effectively suppress flow separation on the airfoil at free-stream speeds in the range from 20 m/s up to 65 m/s. When the speed is 25m/s, the stall angle will be delayed by 3°, lift coefficient will increase and drag coefficient will decrease by 10.4% and 28.9% respectively. Moreover, Experimental results indicate that the threshold voltage increases with the increasing free-stream speed and attack angle. Meanwhile, both of smoke flow visualization and flow control experiments were carried out, conclusions show that the direction of induce flow has little effect on plasma flow control effectiveness, which means that momentum transferring is not the basic cause of active flow control of plasma aerodynamic actuation.

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Neetika Meena et Dr. Sanjay Kumar Jagannath Bagul. « Study on MHD Pulses, Waves, and Instability in Trigging multiple renewables noise on various spectral information scales ». International Journal of Information Technology and Management 18, n^o 2 (3 septembre 2024) : 94–100. http://dx.doi.org/10.29070/8hq93403.

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Major concepts covered in this research include: State of being free vibration and method start changing; MHD waveguides like the magnetic properties dorsal fin, radicular groups, and radicular streaming sites; processes for frequency supplied in imperativeness overflows throughout sub hurricanes and solar activity; the possibility of Heat diffusion resonant frequencies along empty field lines; potential motorists of MHD waves; diagnostic tools of plasma screens with MHD waves; the collaboration of MHD waves mostly with positive ions limits (ionosphere and chromosphere). This review is directed largely at experts in the subjects of magnetosphere material science and solar theoretical physics, while it does delve into the intricacies of the surround investigation fields to those who are concerned. Though there are several noise contributors, aerodynamics is the most significant. When it concerns to aerodynamics noise, the distal end of blades of wind turbines is where the majority of the action occurs. A subject of this research is on blade tip noise caused by wind generators, and an evaluation and comparison of the many methods being used and researched to minimize this difficulty is the paper's primary focus. Subjective assessment outcomes are also compared to quantifiable measurements. Several methods are proposed, and the risks and benefits are compared. Among the most intriguing instances of plasma in reality that we're able to examine close quarters are really the Solar energy, Atmosphere's geomagnetic, and stratosphere. Were very could be used to model such plasmas effectively in principle (MHD). In MHD, the statistics and dynamics of liquids that conduct electricity are hypothetically characterized.

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Cheng Bangqin, 程邦勤, 孙权 Sun Quan, 李军 Li Jun, 苏长兵 Su Changbing et 喻永贵 Yu Yonggui. « Ramp-induced shock wave control through plasma aerodynamic actuation ». High Power Laser and Particle Beams 22, n^o 2 (2010) : 348–52. http://dx.doi.org/10.3788/hplpb20102202.0348.

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MATSUDA, Hisashi, Motofumi TANAKA, Kiyoyuki AMEMORI, Masahiro NOMURA et Toshiki OSAKO. « S056041 Plasma Aerodynamic Control effect on Wind turbine performance ». Proceedings of Mechanical Engineering Congress, Japan 2012 (2012) : _S056041–1—_S056041–5. http://dx.doi.org/10.1299/jsmemecj.2012._s056041-1.

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Ganiev, Y. C., V. P. Gordeev, A. V. Krasilnikov, V. I. Lagutin, V. N. Otmennikov et A. V. Panasenko. « Aerodynamic Drag Reduction by Plasma and Hot-Gas Injection ». Journal of Thermophysics and Heat Transfer 14, n^o 1 (janvier 2000) : 10–17. http://dx.doi.org/10.2514/2.6504.

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Hao, JiangNan, BaLin Tian, YuLin Wang, YaHui Song, ShuCheng Pan et WenFeng Li. « Dielectric barrier plasma dynamics for active aerodynamic flow control ». Science China Physics, Mechanics and Astronomy 57, n^o 2 (3 janvier 2014) : 345–53. http://dx.doi.org/10.1007/s11433-013-5164-8.

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Wu, Xinyi, Yujian Zhang, Deyang Tian, Changju Wu, Jie Zhou et Yunliang Zhu. « Analysis of aerodynamic and stealth characteristics of aircraft under the action of microwave plasma ». Journal of Physics : Conference Series 2764, n^o 1 (1 mai 2024) : 012005. http://dx.doi.org/10.1088/1742-6596/2764/1/012005.

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Abstract This paper investigates the impact of plasma on the aerodynamic and stealth characteristics of hypersonic aircraft. Utilizing the finite volume method, the governing equations of the fluid mechanics were discretized, and the seven-element air chemical reaction model was employed for computations. A technique involving the alteration of the chemical reaction source term rate was employed to replicate the actual plasma concentration distortion phenomena induced by microwaves around hypersonic vehicles, enabling an analysis of the influence of plasma density distortion on the aerodynamic characteristics of these vehicles. In addition, the method of Piecewise Linear JE Recursive Convolution Finite-difference Time-domain (PLJERC-FDTD) is used to calculate the radar scattering cross-section of the target within both the initial and distorted flow fields. This allowed an examination of the variation in the aircraft’s stealth characteristics when exposed to distortion in an ionized environment.

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Rodrigues, Frederico, Mohammadmahdi Abdollahzadehsangroudi, João Nunes-Pereira et José Páscoa. « Recent Developments on Dielectric Barrier Discharge (DBD) Plasma Actuators for Icing Mitigation ». Actuators 12, n^o 1 (21 décembre 2022) : 5. http://dx.doi.org/10.3390/act12010005.

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Ice accretion is a common issue on aircraft flying in cold climate conditions. The ice accumulation on aircraft surfaces disturbs the adjacent airflow field, increases the drag, and significantly reduces the aircraft’s aerodynamic performance. It also increases the weight of the aircraft and causes the failure of critical components in some situations, leading to premature aerodynamic stall and loss of control and lift. With this in mind, several authors have begun to study the thermal effects of plasma actuators for icing control and mitigation, considering both aeronautical and wind energy applications. Although this is a recent topic, several studies have already been performed, and it is clear this topic has attracted the attention of several research groups. Considering the importance and potential of using dielectric barrier discharge (DBD) plasma actuators for ice mitigation, we aim to present in this paper the first review on this topic, summarizing all the information reported in the literature about three major subtopics: thermal effects induced by DBD plasma actuators, plasma actuators’ ability in deicing and ice formation prevention, and ice detection capability of DBD plasma actuators. An overview of the characteristics of these devices is performed and conclusions are drawn regarding recent developments in the application of plasma actuators for icing mitigation purposes.

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Corke, Thomas C., Martiqua L. Post et Dmitry M. Orlov. « SDBD plasma enhanced aerodynamics : concepts, optimization and applications ». Progress in Aerospace Sciences 43, n^o 7-8 (octobre 2007) : 193–217. http://dx.doi.org/10.1016/j.paerosci.2007.06.001.

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He, Wei, Zhong Guo Niu, Bo Pan et Qi Lin. « Experimental Investigation on Improving the Aerodynamic Performance of Swept Aircraft by DBD Plasma ». Applied Mechanics and Materials 110-116 (octobre 2011) : 3234–42. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.3234.

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The experimental investigation on improving the aircraft aerodynamic performance by DBD (Dielectric Barrier Discharges) plasma is described in this paper. The test has been carried out in a low speed wind tunnel with a wept aircraft model. The plasma actuators were set on the upper surface of swept wing combining with airplane body model. The test results presented include the flow field visualization by PIV (Particle Imaging Velocimetry), lift and drag characteristics under the plasma actuators off and on. The results show that the induced flow by DBD plasma may control the separation on the upper surface of the wing evidently, so that the highest stalling angle of the model increases and maximum lift-to-drag ratio rises, respectively. But with the wind velocity increasing, the effect of the plasma decreases gradually.

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Julian, James, Harinaldi, Budiarso, Chin-Cheng Wang et Ming-Jyh Chern. « Effect of plasma actuator in boundary layer on flat plate model with turbulent promoter ». Proceedings of the Institution of Mechanical Engineers, Part G : Journal of Aerospace Engineering 232, n^o 16 (30 août 2017) : 3001–10. http://dx.doi.org/10.1177/0954410017727301.

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This paper shows experimental results for velocity measurement in the boundary layer with the use of a flat plate model. The flat plate model is disrupted with a wire trip and the effect of the plasma actuator to alter the flow in the boundary layer is then observed. The purpose of this research is to characterize the performance of the plasma actuator in a no-flow condition and with the use of a 2 m/s flow and also to theoretically analyze the performance of actuator in the boundary layer namely, displacement thickness, momentum thickness, and energy thickness. This is all done to acquire a deeper understanding of the capabilities of plasma actuator as one of the alternative active flow control equipment and to increase the effect of aerodynamic drag reduction. One of the ways to decrease the aerodynamic drag is to manipulate the flow to have a low boundary layer thickness value in order to prevent an adverse pressure gradient from happening, which then may lead to the formation of a flow separation. From experimental results, it is known that plasma actuator could decrease the thickness of the boundary layer by 9 mm.

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WANG, JIANLEI, HUAXING LI, FENG LIU et SHIJUN LUO. « CHARACTERISTICS OF FORE-BODY SEPARATE FLOW AT HIGH ANGLE OF ATTACK UNDER PLASMA CONTROL ». Modern Physics Letters B 24, n^o 13 (30 mai 2010) : 1401–4. http://dx.doi.org/10.1142/s0217984910023724.

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A pair of plasma actuators with horseshoe shape is proposed for dynamic manipulation of forebody aerodynamic load at high angles of attack. Preliminary wind tunnel pressure measurements show that asymmetric force over a conical forebody with semi-apex angle 10° can be manipulated by activating the plasma actuator mounted on one side of the cone tip. Further work is suggested.

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Hui, Weiwei, Hexiang Zhang, Jianlei Wang, Xuanshi Meng et Huaxing Li. « Heat transfer characteristics of plasma actuation in different boundary-layer flows ». Physics of Fluids 34, n^o 3 (mars 2022) : 034110. http://dx.doi.org/10.1063/5.0084420.

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The coupling characteristics of the aerodynamic and thermal effects of a surface dielectric barrier discharge plasma actuator and its transfer characteristics in different boundary-layer flows are studied experimentally. The actuator is attached to the surface of a flat-plate airfoil and driving by an alternative-current signal. Different boundary-layer flows are achieved in the wind tunnel by adjusting the airfoil's angle of attack with a Reynolds number of 2.02 × 105. The spatial temperature-rise distributions and velocity fields induced by plasma actuation in quiescent air show that the influence range of temperature is consistent with that of the induced velocity field. The aerodynamic and thermal effects induced by plasma actuation have strong coupling characteristics. The heat around the actuator is limited within the boundary-layer flows with a 15 m/s incoming flow. The temperature rise outside the boundary layer is close to zero. In the turbulent boundary-layer flow, the temperature is lower than that in the laminar boundary-layer flow as a whole. The maximum temperature-rise difference exceeds 10 °C. In the leading-edge separation-bubble flow, most heat generated by the plasma actuation is restricted inside the separation bubble. The results provide references for the mechanism detection of related plasma icing-control and flow-control research.

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Lee, Changwook, Ju-Hyeong Sim, Sunghyun Han, Su Hwan Yun et Taegyu Kim. « Aerodynamic Drag Reduction in Cylindrical Model Using DBD Plasma Actuator ». Journal of the Korean Society of Propulsion Engineers 19, n^o 1 (1 février 2015) : 25–32. http://dx.doi.org/10.6108/kspe.2015.19.1.025.

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Bisek, Nicholas J., Iain D. Boyd et Jonathan Poggie. « Numerical Study of Plasma-Assisted Aerodynamic Control for Hypersonic Vehicles ». Journal of Spacecraft and Rockets 46, n^o 3 (mai 2009) : 568–76. http://dx.doi.org/10.2514/1.39032.

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Sun, Quan, Bangqin Cheng, Yinghong Li, Wei Cui, Di Jin et Jun Li. « Experimental Investigation on Airfoil Shock Control by Plasma Aerodynamic Actuation ». Plasma Science and Technology 15, n^o 11 (novembre 2013) : 1136–43. http://dx.doi.org/10.1088/1009-0630/15/11/11.

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Sun, Quan, Bangqin Cheng, Yinghong Li, Wei Cui, Yonggui Yu et Junhun Jie. « Experimental Investigation of Hypersonic Flow and Plasma Aerodynamic Actuation Interaction ». Plasma Science and Technology 15, n^o 9 (septembre 2013) : 908–14. http://dx.doi.org/10.1088/1009-0630/15/9/15.

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MATSUI, Masazumi, Noboru FUJITA, Kengo MAEDA et Takashi MATSUNO. « 806 Numerical Analysis of Aerodynamic Control Performance Using Plasma Actuators ». Proceedings of Conference of Chugoku-Shikoku Branch 2014.52 (2014) : _806–1_—_806–3_. http://dx.doi.org/10.1299/jsmecs.2014.52._806-1_.

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Zhu, Yifei, Yun Wu, Wei Cui, Yinghong Li et Min Jia. « Modelling of plasma aerodynamic actuation driven by nanosecond SDBD discharge ». Journal of Physics D : Applied Physics 46, n^o 35 (16 août 2013) : 355205. http://dx.doi.org/10.1088/0022-3727/46/35/355205.

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Sun, Quan, YingHong Li, Wei Cui, BangQin Cheng, Jun Li et Hui Dai. « Shock wave-boundary layer interactions control by plasma aerodynamic actuation ». Science China Technological Sciences 57, n^o 7 (16 juin 2014) : 1335–41. http://dx.doi.org/10.1007/s11431-014-5586-1.

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