Open Access Open Access  Restricted Access Subscription or Fee Access

Flow Separation Delay on NACA 4415 Airfoil Using Plasma Actuator Effect

(*) Corresponding author

Authors' affiliations



Flow separation is a phenomenon that greatly affects the airfoil performance due to adverse pressure gradient. The loss in kinetic energy behind the separated flow region causes undesirable effects, contributing greatly to the increased drag force. In order to overcome this condition, one of the alternative methods is to provide momentum into the fluid in order to counter the adverse pressure gradient thus eliminating the flow separation. This paper discusses the use of plasma actuator located at 0.21 c from leading edge of an airfoil NACA 4415. The investigated areas are the ones of Reynolds numbers 35,000, 100,000, and 200,000. This study uses experimental method. Load cells have been used to obtain aerodynamic force thus the data have been validated from computational methods. In addition, there is also flow visualization in order to understand the flow phenomenon through the testing model. The results of this experimental study show that plasma actuator can increase the value of lift coefficient (CL) and decreasing drag coefficient with the average increase of CL is 24.90%, 7.81% and 1.37%, and also the average decrease is CD is 8.45%, 0.86% and 1.96% in each variation of Reynolds number. The best result is found at Re 35,000 and it is adequate to produce the best separation delay point of 0.0107 c at α = 9°.
Copyright © 2019 Praise Worthy Prize - All rights reserved.


Separation; Airfoil; Plasma; Reynolds Number

Full Text:



Sung, Y., Kim, W., Mungal, M. G., & Cappelli, M. A. (2006). Aerodynamic modification of flow over bluff objects by plasma actuation, Experiments in fluids, 41(3), 479-486.

Gad-el-Hak, M. Flow Control: Passive, Active, and Reactive Flow Management. 2000.

Little, J., Nishihara, M., Adamovich, I., & Samimy, M. (2010). High-lift airfoil trailing edge separation control using a single dielectric barrier discharge plasma actuator, Experiments in fluids, 48(3), 521-537.

Fransson, J. H., Konieczny, P., & Alfredsson, P. H. (2004). Flow around a porous cylinder subject to continuous suction or blowing. Journal of Fluids and Structures, 19(8), 1031-1048.

Yousefi, K., & Saleh, R. (2014). The effects of trailing edge blowing on aerodynamic characteristics of the NACA 0012 airfoil and optimization of the blowing slot geometry. Journal of Theoretical and Applied Mechanics, 52(1), 165-179.

Tebbiche, H., & Boutoudj, M. S. (2014). Vortex Generators Contribution to the enhancement of the Aerodynamic Performances. Advanced Materials Research, 950.

Zong, H. H., Cui, W., Wu, Y., Zhang, Z. B., Liang, H., Jia, M., & Li, Y. H. (2015). Influence of capacitor energy on performance of a three-electrode plasma synthetic jet actuator. Sensors and Actuators A: Physical, 222, 114-121.

Julian, J., Harinaldi, Budiarso (2016). The Effect of Plasma Actuator Utilization to The Reduction of Aerodynamic Drag of Cylinder and Box Models, 12th Int. Conf. on Heat Transfer, Fluid Mechanics and Thermodynamics, pp. 833-838.

Corke, T. C., Enloe, C. L., & Wilkinson, S. P. (2010). Dielectric barrier discharge plasma actuators for flow control. Annual review of fluid mechanics, 42, 505-529.

Patel, M. P., Sowle, Z. H., Corke, T. C., & He, C. (2007). Autonomous sensing and control of wing stall using a smart plasma slat. Journal of aircraft, 44(2), 516-527.

Sun, M., Yang, B., Zhang, Z. T., & Lei, M. K. (2013). Experimental study on flow hysteresis effect on NACA0015 airfoil using DBD plasma actuator. Surface and Coatings Technology, 228, S179-S183.

Julian, J., Harinaldi, Budiarso, Difitro, R., & Stefan, P. (2016). The Effect of Plasma Actuator Placement on Drag Coefficient Reduction of Ahmed Body as An Aerodynamic Model. International Journal of Technology, 7(2), 306-313.

Plogmann, B., Mack, S., & Fasel, H. F. (2009, June). Experimental investigation of open-and closed-loop control for airfoil under low reynolds number conditions. In 39th AIAA Fluid Dynamics Conference (p. 4282).

Bouremel, Y., Li, J. M., Zhao, Z., & Debiasi, M. (2013). Effects of AC Dielectric Barrier Discharge plasma actuator location on flow separation and airfoil performance. Procedia Engineering, 67, 270-278.

Harinaldi, M., & Eng, M. (2005). Statistical principles for engineering and science. Jakarta: Erlangga.

Bardera-Mora, R., Conesa, A., Sánchez García, M., Flow Separation Control with a Plasma Actuator Over a Metallic NACA 4418, (2017) International Review of Aerospace Engineering (IREASE), 10 (6), pp. 308-314.

Conesa Torres, A., Bardera-Mora, R., Sánchez García, M., León Calero, M., 3D Backward-Facing Step Flow Structure Modification with Plasma Actuators, (2017) International Review of Aerospace Engineering (IREASE), 10 (1), pp. 14-23.

Julian, J., Karim, R., Budiarso, B., Harinaldi, H., Review: Flow Control on a Squareback Model, (2017) International Review of Aerospace Engineering (IREASE), 10 (4), pp. 230-239.


  • There are currently no refbacks.

Please send any question about this web site to
Copyright © 2005-2023 Praise Worthy Prize