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

Shahrbabaki, Amin Nazarian; Bazazzadeh, Mehrdad; Khoshkhoo, R.

doi:10.1155/2021/2047162

Cited by 6 publications

(3 citation statements)

References 39 publications

(33 reference statements)

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“…On the other hand, one of the important problems, both from a fundamental and practical point of view, is the possibility of switching between the solutions of two types. In practical applications, heating (or cooling) some areas of the flow using various methods is often used in flow control [21][22][23][24].…”

Section: Introductionmentioning

confidence: 99%

Dual Numerical Solution for 3D Supersonic Laminar Flow Past a Blunt-Fin Junction: Change in Temperature Ratio as a Method of Flow Control

Kolesnik

Смирнов

Babich

2023

Fluids

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The results of a numerical solution of the problem of supersonic flow past a blunt fin mounted on a plate with a developing boundary layer are presented. The initial formulation of the problem is based on the presented in the literature computational and experimental investigation, in which the laminar flow regime was studied for the fin perpendicular to the plate at the free-stream Mach number equal to 6.7. Earlier, the authors showed (2020) that under these conditions there exist two stable solutions to the problem. These solutions correspond to the metastable states of flow with different configurations of the vortex structure and different patterns of local heat transfer. In the present study, the influence of a temperature ratio on the vortex structure in the separation region, local heat transfer, and the possibility of obtaining a dual solution are investigated. The ability to switch between solutions of two types using a short-time change in the plate temperature ratio are shown.

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Section: Introductionmentioning

confidence: 99%

Dual Numerical Solution for 3D Supersonic Laminar Flow Past a Blunt-Fin Junction: Change in Temperature Ratio as a Method of Flow Control

Kolesnik

Смирнов

Babich

2023

Fluids

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“…In fact, the three effects often exist at the same time. Recent studies using torch plasma, filamentary discharge, microwave discharge, low-frequency arc discharge, streamer high-frequency (HF) discharges, surface discharges, and nanosecond pulsed discharges (NSDs) [20] have shown that plasma can enhance ignition, flame stabilization, and fuel/air mixing via chemical, thermal, and plasma-induced aerodynamic effects [21][22][23][24].…”

Section: Introductionmentioning

confidence: 99%

Influence of Plasma on the Combustion Mode in a Scramjet

Meng

Chen

2022

Aerospace

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To examine the plasma-assisted combustion of a scramjet, a microwave-enhanced gliding arc plasma method was proposed in this study, and the flame structure and combustion instability were observed. The mechanism of plasma-assisted combustion was obtained via a Bunsen experiment, and then the influence on supersonic combustion was obtained on a direct-connected scramjet. The active species of the flame was determined via optical emission spectroscopy, and the flame temperature was measured with a thermocouple. The luminous intensity of the OH radicals in the flame increased ninefold when the flame temperature was increased to 1573 K, but the luminous intensity of CH* and C2 was not obviously changed with the excitation of arc plasma. Moreover, the DC arc plasma had no effect on the rotation and the vibration temperature of OH radicals under these experimental conditions. In the range of microwave energy less than 800 W, there was no typical change in the intensity of the radicals; however, when the microwave power was up to 1000 W, the effect became obvious. When plasma was applied to the scramjet, the plasma caused the pre-combustion shock train to move forward, and the initial and stable position of the flame was transferred from the cavity shear layer to the front of the fuel jet. These results clearly show that plasma free radical mechanisms cause changes to combustion modes.

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“…Flow separation reduces the aerodynamic efficiency. Passive or active device has been used to control separated flow [5][6][7][8]. A VG is a passive device [9].…”

Section: Introductionmentioning

confidence: 99%

Separation Control for a Transonic Convex Corner Flow Using Ramp-Type Vortex Generators

Chung

Исаев

2022

International Journal of Aerospace Engineering

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A flap can be used to control wing camber and as a high-lift device. A convex corner is a simplified model of the upper surface of a flap. At transonic speeds, shock-induced boundary layer separation (SIBLS) occurs at greater freestream Mach numbers and deflection angles. This results in energy losses and a reduction in aerodynamic performance. This study installs ramp-type vortex generators (VGs) upstream of a convex corner, and the effect of the height of the VG on SIBLS is determined. As the height of the VG increases, the magnitude of the mean surface pressure upstream of the corner increases and downstream expansion decreases, which results in a reduction in lift. A reduction in peak surface pressure fluctuations, the separation length, and the frequency of shock oscillation is also determined. For flow control and lift enhancement, micro-VGs are more effective.

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

Cited by 6 publications

References 39 publications

Dual Numerical Solution for 3D Supersonic Laminar Flow Past a Blunt-Fin Junction: Change in Temperature Ratio as a Method of Flow Control

Dual Numerical Solution for 3D Supersonic Laminar Flow Past a Blunt-Fin Junction: Change in Temperature Ratio as a Method of Flow Control

Influence of Plasma on the Combustion Mode in a Scramjet

Separation Control for a Transonic Convex Corner Flow Using Ramp-Type Vortex Generators

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