Numerical Study of Stream-wise and Span-wise Nanosecond DBD Plasma Actuators Effects on Supersonic Flow Separation

Document Type : Regular Article


Faculty of Mechanical Engineering, Malek Ashtar University of Technology, Iran



The current paper aimed to investigate the primary control mechanism of various Nanosecond Dielectric Barrier Discharge (NS-DBD) plasma actuators on the Shock Wave/Boundary Layer Interaction (SWBLI). For this purpose, the effects of the NS-DBD actuator have been investigated on an M=2.8 supersonic flow numerically. The Reynolds Averaged Navier-Stokes (RANS) equations and  SST turbulence model were used as the governing equations to simulate the supersonic flow characteristics. The numerical simulation of the baseline flow (without plasma actuator) was verified using an investigation on wall pressure distribution and the size of SWBLI. Then, NS-DBD phenomenological model based on the energy deposition model in accordance with experimental data was applied to the baseline simulation. Moreover, various stream-wise and span-wise NS-DBD plasma actuator models were used to investigate the actuator effects on the studied flow’s low-density separation zone. Comparing the numerical results of the stream-wise and span-wise actuations revealed that both actuator types cause a momentum transferred to the flow, consequently decreasing the SWBLI region’s size and the boundary layer’s thickness. The results showed that the presence of the NS-DBD actuator increased the local temperature of flow over the insulated electrode. In this regard, a stream-wise NS-DBD actuator with a length of 90 mm upstream of the SWBLI increased the separation flow velocity by 33.7% and decreased the length of the separation region by 5 mm. Also, in this case, after 170 microseconds from the start of actuation, the size of SWBLI decreased by 4.2 mm. Therefore, it can be concluded that the stream-wise type of actuation was more effective in reducing the flow separation and SWBLI size than the span-wise type due to vortex generation into the inlet flow and suppressing the SWBLI region. The proposed NS-DBD actuators were mainly capable of applying the momentum to the boundary layer and reducing the velocity of separated flow in the SWBLI zone. The micro shock wave propagation through the flow associated with the NS-DBD discharge of the actuators can produce more effective high-speed flow control.


Abdollahzadeh, M., J. C. Páscoa and P. J. Oliveira (2014). Two-dimensional numerical modeling of interaction of micro-shock wave generated by nanosecond plasma actuators and transonic flow. Journal of Computational and Applied Mathematics 270, 401–416.##
Anzalotta, C., K. Joshi, E. Fernandez and S. Bhattacharya (2020). Effect of forcing the tip-gap of a NACA0065 airfoil using plasma actuators: A proof-of-concept study.  Aerospace Science and Technology 107, 106268.##
Chen, K., X. Geng, Z. Shi, K. Cheng and H. Cui (2020). Experimental investigation of influence of sliding discharge DBD plasma on low-speed boundary layer. AIP Advances 10, 35108##
Chen, T. Y., A. C. Rousso, S. Wu, B. M. Goldberg, H. Van Der Meiden, Y. Ju and E. Kolemen (2019). Time-resolved characterization of plasma properties in a CH4/He nanosecond-pulsed dielectric barrier discharge. Journal of Physics D: Applied Physics 52, 18LT02.##
Duraisamy, K., G. Iaccarino and H. Xiao (2019). Turbulence modeling in the age of data. Annual Review of Fluid Mechanics 51, 357–377.##
Falempin, F., A. A. Firsov, D. A. Yarantsev, M. A. Goldfeld, K. Timofeev and S. B. Leonov (2015). Plasma control of shock wave configuration in off-design mode of M = 2 inlet. Experiments in Fluids 56(54).##
Falempin, F., E. Wendling, M. Goldfeld and A.  Starov (2006). Experimental Investigation of Starting Process for a Variable Geometry Air Inlet operating from Mach 2 to Mach 8.  In: 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. American Institute of Aeronautics and Astronautics, California, USA.##
Gaitonde, D. V. (2013). Analysis of plasma-based flow control mechanisms through large-eddy simulations. Computers & Fluids 85, 19–26.##
Huang, J., B. Hu, Z. Li, J. Zhang, Z. Qian and S. Lan (2020). The Effects of Plasma-Based Body Force on Flow Separation Suppression. Advances in Effective Flow Separation Control for Aircraft Drag Reduction. Modeling, Simulations and Experimentations, Book Chapter, Springer International Publishing.##
Khoshkhoo, R. and A. Jahangirian (2016). Numerical Simulation of Flow Separation Control using Multiple DBD Plasma Actuators. Journal of Applied Fluid Mechanics 9(4), 1865-1875.##
Kinefuchi, K., A. Y. Starikovskiy and R. B. Miles (2017). Control of shock-wave/boundary-layer interaction using nanosecond-pulsed plasma actuators. Journal of Propulsion and Power 34, 909–919.##
Kinefuchi, K., A. Y. Starikovskiy and R. B. Miles (2018). Numerical investigation of nanosecond pulsed plasma actuators for control of shock-wave/boundary-layer separation. Physics of Fluids 30,106105.##
Kolbakir, C., H. Hu, Y. Liu and H. Hu (2020). An experimental study on different plasma actuator layouts for aircraft icing mitigation. Aerospace Science and Technology 107, 106325.##
Lee, S., E. Loth and H. Babinsky (2011). Normal shock boundary layer control with various vortex generator geometries. Computers & Fluids 49, 233–246.##
Liao, Y., I. V. Mursenkova, I. E. Ivanov, I. A. Znamenskaya and N. N. Sysoev (2020). Shock waves generated by a pulsed surface sliding discharge in a supersonic airflow past a wedge. Physics of Fluids 32, 106108.##
Mishra, B. K. and P. K. Panigrahi (2020). Flow field induced by a dielectric barrier discharge plasma actuator analyzed with bi-orthogonal decomposition. Physics of Fluids 32.##
Orr, K., X. Yang, C. Richards, E. Jans, S. Raskar, D. C. van den Bekerom and I. V. Adamovich (2021). Characterization and Kinetic Modeling of Ns Pulse and Hybrid Ns Pulse/RF Plasmas. In: AIAA Scitech 2021 Forum, P. 683.##
Panaras, A. G. and F. K. Lu (2015). Micro-vortex generators for shock wave/boundary layer interactions. Progress in Aerospace Science, Vol. 74, pp. 16–47.##
Pirozzoli, S. and F. Grasso (2006). Direct numerical simulation of impinging shock wave/turbulent boundary layer interaction at M=2.25. Physics of Fluids 18.##
Roupassov, D. V, Nikipelov, A. A., Nudnova, M. M., Starikovskii, A. Y. (2009). Flow separation control by plasma actuator with nanosecond pulsed-periodic discharge. AIAA Journal 47, 168–185.##
Saad, R., E. Erdem, L. Yang and K. Kontis (2012). Experimental Studies on Micro-ramps at Mach. 28th International Symposium on Shock Waves, Manchester UK, pp 861-866.##
Sarimurat, M. N. and T. Q. Dang (2012). Shock Management in Diverging Flow Passages by Blowing/Suction, Part 2: Applications. Journal of Propulsion and Power 28, 1230–1242.##
Shinde, V., J. McNamara and D. Gaitonde (2020). Control of transitional shock wave boundary layer interaction using structurally constrained surface morphing. Aerospace Science Technology 96, 105545.##
Smits, A. J. and J. P. Dussauge (2006). Turbulent shear layers in supersonic flow. Springer Science & Business Media.##
Smith, A. N., Babinsky, H. and Fulker, J. L. (2004). Ashill, P.R.: Shock Wave/ Boundary-Layer Interaction Control Using Streamwise Slots in Transonic Flows. Journal of Aircraft 41, 540–546.##
Starikovskii, A. Y., A. A. Nikipelov, M. M. Nudnova and D. V. Roupassov (2009). SDBD plasma actuator with nanosecond pulse-periodic discharge. Plasma Sources Science and Technology 18, 34015.##
Takashima, K., Y. Zuzeek, W. R. Lempert and I. V. Adamovich (2011). Characterization of a surface dielectric barrier discharge plasma sustained by repetitive nanosecond pulses. Plasma Sources Science and Technology 20, 55009.##
Taleghani, A. S., A. Shadaram, M. Mirzaei and S. Abdolahipour (2018). Parametric study of a plasma actuator at unsteady actuation by measurements of the induced flow velocity for flow control. Journal of the Brazilian Society of Mechanical Sciences and Engineering 40(173).##
Unfer, T. and J. P. Boeuf (2009). Modelling of a nanosecond surface discharge actuator. Journal of Physics D: Applied Physics 42, 194017.##
Veerakumar, R., V. Raul, Y. Liu, X. Wang, L. Leifsson and H. Hu (2020). Metamodeling-based parametric optimization of DBD plasma actuation to suppress flow separation over a wind turbine airfoil model. Acta Mechanica Sinica 36, 260–274.##
Verma, S. B. and C. Manisankar (2018). Control of a Mach reflection-induced interaction using an array of vane-type vortex generators. Shock Waves 28, 815–828 .##
Webb, N. J. (2010). Control of Supersonic Mixed-Compression Inlets Using Localized Arc Filament Plasma Actuators. MSc. Thesis, The Ohio State University.##
Wei, B., Y. Wu, H. Liang, J. Chen, G. Zhao, M. Tian and H. Xu (2019). Performance and mechanism analysis of nanosecond pulsed surface dielectric barrier discharge based plasma deicer. Phys. Fluids. 31.##
Whalen, T .J., A. G. Schöneich, S. J. Laurence, B. T. Sullivan, D. J. Bodony, M. Freydin, E. H. Dowell and G. M. Buck (2020). Hypersonic fluid-structure interactions in compression corner shock wave  boundary layer interaction. AIAA Journal 58,  4090–4105.##
Wilcox, D. C. (2006). Trbulence Modeling for CFD. DCW Industries.##
Wilde, N. D., H. Xu, N. Gomez-Vega and S. R. H. Barrett (2021). A model of surface dielectric barrier discharge power. Applied Physics Letters 118, 154102.##
Zheng, J. G., Z. J. Zhao, J. Li, Y. D. Cui and B. C. Khoo (2014). Numerical simulation of nanosecond pulsed dielectric barrier discharge actuator in a quiescent flow. Physics of Fluids 26.##
Znamenskaya, I., D. Tatarenkova, T. Kuli-zade and I. Ivanov (2020). Nanosecond discharges in a non-stationary flow around an obstacle.  Journal of Physics: Conference Series. 12002.##
Volume 15, Issue 4 - Serial Number 66
July and August 2022
Pages 1035-1047
  • Received: 22 December 2021
  • Revised: 12 February 2022
  • Accepted: 20 February 2022
  • Available online: 11 May 2022