Direct Numerical Simulation of the Pulsed Arc Discharge in Supersonic Compression Ramp Flow

Song, Guoxing; Li, Jun; Tang, Mengxiao

doi:10.1007/s11630-020-1380-5

Cited by 4 publications

(2 citation statements)

References 37 publications

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“…In recent years, arrayed pulsed energy depositions based on nanosecond/microsecond pulsed discharges have been attempted for high-speed flow controls [19,20], which are considered potential approaches to improve supersonic flow qualities. They can induce consistently heated gases that propagate downstream and are gradually expanding during their propagation.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study on Effects of Arrayed Pulsed Energy Depositions on a Supersonic Combustor

Cai

Gao

Wang

et al. 2022

International Journal of Aerospace Engineering

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This paper proposes a method to improve the mixing efficiency of a supersonic combustor by using arrayed pulsed energy depositions, and this method is verified by a numerical simulation. In the simulation, the Navier-Stokes equations with an energy source are solved to simulate the effects of energy depositions in various distributions on the fuel mixture in the combustor. It is found that the energy deposition arranged in the streamwise direction leads to a significant improvement in the mixing efficiency and maximum concentration decay rate of the ethylene fuel by increasing the scale of the jet-induced counter-rotating vortex pair. The energy deposition arranged in the spanwise direction introduces another counter-rotating vortex pair which can also contribute to the fuel mixture. By comparison, the energy deposition distributed in the streamwise direction and downstream of the jet orifice is shown to be the most effective case in the fuel mixing enhancement. Under the energy deposition, the wall pressure on the trailing edge of the cavity is increased which leads to a decrease in the total pressure recovery of the combustor, but this decrease is not significant.

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Section: Introductionmentioning

confidence: 99%

Numerical Study on Effects of Arrayed Pulsed Energy Depositions on a Supersonic Combustor

Cai

Gao

Wang

et al. 2022

International Journal of Aerospace Engineering

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“…NS-DBD plasma actuators, spark jet, and arc plasma are among conventional thermal actuators [24,25]. NS-DBD has a high-voltage DC input with nanosecond pulses with a specific frequency.…”

Section: Introductionmentioning

confidence: 99%

Investigation on Supersonic Flow Control Using Nanosecond Dielectric Barrier Discharge Plasma Actuators

Shahrbabaki

Bazazzadeh

Khoshkhoo

2021

International Journal of Aerospace Engineering

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In this paper, the effects of streamwise Nanosecond Dielectric Barrier Discharge (NS-DBD) actuators on Shock Wave/Boundary Layer Interaction (SWBLI) are investigated in a Mach 2.5 supersonic flow. In this regard, the numerical investigation of NS-DBD plasma actuator effects on unsteady supersonic flow passing a 14° shock wave generator is performed using simulation of Navier-Stokes equations for 3D-flow, unsteady, compressible, and k ‐ ω SST turbulent model. In order to evaluate plasma discharge capabilities, the effects of plasma discharge length on the flow behavior are studied by investigating the flow friction factor, the region of separation bubble formation, velocity, and temperature distribution fields in the SWBLI region. The numerical results showed that plasma discharge increased the temperature of the discharge region and boundary layer temperature in the vicinity of flow separation and consequently reduced the Mach number in the plasma discharge region. Plasma excitation to the separation bubbles shifted the separation region to the upstream around 6 mm, increased SWBLI height, and increased the angle of the separation shock wave. Besides, the investigations on the variations of pressure recovery coefficient illustrated that plasma discharge to the separation bubbles had no impressive effect and decreased pressure recovery coefficient. The numerical results showed that although the NS-DBD plasma actuator was not effective in reducing the separation area in SWBLI, they were capable of shifting the separation shock position upstream. This feature can be used to modify the structure of the shock wave in supersonic intakes in off-design conditions.

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Experimental investigation on compression ramp shock wave/boundary layer interaction control using plasma actuator array

Tang

Zong

et al. 2021

Physics of Fluids

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Particle image velocimetry measurement on shock wave/boundary layer interaction in a Mach 2.0 supersonic wind tunnel is performed to quantitatively reveal the plasma flow control effect in this paper. The typical flow structure is produced by a 24-degree compression ramp model and the streamwise plasma actuator array with five pulsed spark discharge plasma actuators is adopted as the control device. In the midspan plane, the results show that although the separation region exhibits an obvious extension, the foot of the separation wave moves upstream and the shock wave angle decreases from 41.6° to 22.3°, proving the decline in shock intensity. The shock wave drag is estimated to be reduced by 45%. According to the phase-averaged velocity field, the reason that the high-frequency actuation plays a key role in achieving the continuous control effect is revealed through the temporal evolution of the separation region area. Also, another interesting phenomenon that the flow deflects when passing through the actuation region is found, which may induce the upwash and downwash motions of the boundary layer and further reduce the flow separation on both sides of the actuation region. At last, a preliminary conceptual model is proposed to reveal the probable flow control mechanism.

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Direct Numerical Simulation of the Pulsed Arc Discharge in Supersonic Compression Ramp Flow

Cited by 4 publications

References 37 publications

Numerical Study on Effects of Arrayed Pulsed Energy Depositions on a Supersonic Combustor

Numerical Study on Effects of Arrayed Pulsed Energy Depositions on a Supersonic Combustor

Investigation on Supersonic Flow Control Using Nanosecond Dielectric Barrier Discharge Plasma Actuators

Experimental investigation on compression ramp shock wave/boundary layer interaction control using plasma actuator array

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