Gnapowski Ernest, Pytka Jarosław, Józwik Jerzy, Laskowski Jan, Michałowska Joanna
Faculty of Technical Sciences, University College of Enterprise and Administration, 20-150 Lublin, Poland.
Faculty of Mechanical Engineering, Lublin University of Technology, 20-618 Lublin, Poland.
Sensors (Basel). 2021 Jan 7;21(2):363. doi: 10.3390/s21020363.
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 = 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.
该手稿介绍了在具有SD 7003翼型的机翼模型上进行的实验研究。一个带有介质阻挡放电（DBD）的等离子体致动器被放置在机翼表面以控制边界层。实验测试在航空实验室风洞中进行，在测试过程中测量作用在机翼上的力。所进行的实验研究涉及分析在关闭和开启DBD等离子体致动器时机翼表面发生的现象。实验测试中使用的等离子体致动器与传统等离子体致动器相比具有不同的结构。通常测试的等离子体致动器使用固体/不可渗透电极，而在该研究中，等离子体致动器使用一种新型电极，即由不可渗透的聚酰亚胺电介质隔开的两个网状电极。实验研究在攻角α = 15°以及几种风速 = 5 - 15 m/s（步长为5 m/s）的条件下进行，雷诺数Re = 87,500 - 262,500。SD 7003翼型具有最大升力系数时的临界攻角约为11°；在实验研究中，攻角为15°。尽管攻角较大，但仍有可能提高升力系数。使用带有两个网状电极的等离子体致动器即使在大攻角下也能使升力增加5%。在实验研究中，使用高压电源为DBD等离子体致动器供电，电压范围为7.5至15 kV。
