Computational Analysis of Dielectric Barrier Discharge Plasma Actuator Impact on Airfoil Characteristics | ||||
| Journal of International Society for Science and Engineering | ||||
| Volume 6, Issue 1, March 2024, Page 18-25 PDF (2.03 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/jisse.2024.308481.1092 | ||||
 View on SCiNiTO | ||||
| Authors | ||||
Amr Ahmed El-Feky  1; Deyaa Nabil2; Kamal Hagag3
| ||||
| 1Mechanical Engineering Department , National Research Centre, Egypt | ||||
| 2Cairo University | ||||
| 3Nuclear Research Center | ||||
| Abstract | ||||
| In recent years, Plasma actuators have strengthened the ability to control flows in creative manners leading to improvements in lift, drag reduction, and aerodynamic efficiency. These advancements could result in safe, more effective, and quiet aircraft. A numerical investigation is performed to determine the influence of Dielectric barrier Discharge (DBD) plasma on the flow properties of NACA 0012 airfoil at low Reynolds numbers, considering various angles of attack. The modified baseline airfoil was examined at three applied voltages 6.85 kV, 8.38 kV, and 11.45 kV at constant frequency. The results demonstrated that, when compared to the baseline airfoil, the DBD plasma actuator delays the trailing edge flow separation. Moreover, at 11.45 kV, the flow maintains attached to the airfoil at an angle of 20º and entirely eliminating the flow separation. Furthermore, the DBD airfoil significantly rising the lift coefficients while reducing the drag coefficients. | ||||
| Keywords | ||||
| DBD Actuator; Flow Separation; NACA 0012; Lift Coefficient Drag Coefficient | ||||
|
Statistics Article View: 125 PDF Download: 149 |
||||
