Suppressing a Laminar Flow Separation Zone by Spark Discharge at Mach Number M = 1.43

Polivanov, P. A.; Sidorenko, A. A.

doi:10.1134/s1063785018090262

Cited by 10 publications

(3 citation statements)

References 7 publications

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“…When a sufficient amount of power is introduced into the flow, such an action can be classified as "flow control". There are numerous studies available in which electric discharges have been used for controlling SWBLI [5,44]. For instance, Narayanaswamy et al [45] employed a pulsed plasma jet array actuator to control the separation shock wave of SWBLI on a compression ramp.…”

Section: Introductionmentioning

confidence: 99%

Response of the Shock Wave/Boundary Layer Interaction to Disturbances Induced by the Plasma Discharge

Vishnyakov,

Polivanov,

Sidorenko

2023

Aerospace

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The paper focuses on the investigation of unsteady effects in shock wave/boundary layer interaction. The study was carried out using a flat plate model subjected to a free stream Mach number of 1.43 and a unit Reynolds number (Re1) of 11.5 × 106 1/m. To generate two-dimensional disturbances in the laminar boundary layer upstream of the separation region, a dielectric barrier discharge was employed. The disturbances were generated within the frequency range of 500 to 1700 Hz. The Strouhal numbers based on the length of the separation bubble ranged from 0.04 to 0.13. The measurements were carried out using a hot-wire anemometer. Analysis of the data shows that disturbances in this frequency range mostly decay. The maximum amplitudes of perturbations were observed at frequencies of 1250 Hz and 1700 Hz.

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Section: Introductionmentioning

confidence: 99%

Response of the Shock Wave/Boundary Layer Interaction to Disturbances Induced by the Plasma Discharge

Vishnyakov,

Polivanov,

Sidorenko

2023

Aerospace

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“…However, attention was placed on the development of unstable modes triggered by discharge, and plasma actuation was never used as a direct method to introduce sufficiently strong disturbances which force boundary-layer transition in a short distance. To date, only Polivanova & Sidorenko (2018) have tried to utilize spark discharge triggered flow transition as a mean to suppress laminar flow separation. Although promising results have been demonstrated in terms of the variation of separated flow, the physics pertaining to plasma-induced laminar-turbulent transition remains unclear.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of supersonic boundary-layer tripping with a spanwise pulsed spark discharge array

Tang

Zong

et al. 2021

J. Fluid Mech.

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In this paper, a pulsed spark discharge plasma actuator array is deployed to control laminar–turbulent transition in a Mach 3.0 flat-plate boundary layer, and the subtle flow structures are visualized by nanoparticle planar laser scattering (NPLS) technique. Results show that the onset location of turbulence can be brought upstream by plasma actuation, corresponding to forced boundary-layer transition. Hairpin vortex packets evolved from the thermal bulbs play a vital role in the breakdown of laminar flow. With the help of a machine learning tool, all the relevant structures induced by plasma actuation are extracted from NPLS images, and a conceptual model of the hairpin vortex generation is proposed, including three stages: production and lift-up of the high-vorticity region, formation of the $\varLambda$ vortex and evolution of the hairpin vortex.

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“…Most of control methods are based on modifying the boundary layer. For instance, in studies [6,7] plasma actuators were used to suppress the separation zones by intensifying the mass exchange between the external flow and boundary layer [6] or by turbulizing the flow [7]. In solving these tasks, the interest in using blowing/suction through the perforated surface is reduced to more detailed consideration of the technological aspects of the issue.…”

mentioning

confidence: 99%

Numerical and experimental study of the effect of gas blowing/suction through a perforated surface on the boundary layer at a supersonic Mach number

Polivanov

2022

Technical Physics Letters

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In this paper a numerical and experimental study of the effect of blowing/suction through a perforated surface on a turbulent boundary layer at a Mach number M=1.4 was carried out. Most of the calculations were performed by Reynolds-averaged Navier-Stokes equations with the kappa-ω SST turbulence model. The calculated geometry completely repeated the experimental one including the perforated surface. The numerical data were compared with experimental measurements obtained by the PIV method. Analysis of the data made it possible to find the limits of applicability of the numerical method for the flow under study. Keywords: supersonic flow, gas blowing/suction through a perforated surface, boundary layer, turbulence model kappa-ω SST, PIV method.

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Suppressing a Laminar Flow Separation Zone by Spark Discharge at Mach Number M = 1.43

Cited by 10 publications

References 7 publications

Response of the Shock Wave/Boundary Layer Interaction to Disturbances Induced by the Plasma Discharge

Response of the Shock Wave/Boundary Layer Interaction to Disturbances Induced by the Plasma Discharge

Experimental investigation of supersonic boundary-layer tripping with a spanwise pulsed spark discharge array

Numerical and experimental study of the effect of gas blowing/suction through a perforated surface on the boundary layer at a supersonic Mach number

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