On the Problem of Using Particle Image Velocimetry for Measurements in High-Velocity Thin Shear Layers

Vishnyakov, O. I.; Polivanov, P. A.; Sidorenko, A.A.

doi:10.1134/s0021894420050089

Cited by 6 publications

(1 citation statement)

References 13 publications

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“…These challenges primarily stem from the high computational costs associated with simulating flows at large Reynolds numbers over extended periods of time to accumulate sufficient statistics for analyzing low-frequency flow pulsations [13]. Consequently, experimental investigations of this phenomenon remain highly relevant, especially considering the availability of modern measurement techniques such as hot-wire anemometry and PIV [38][39][40] that provide extensive data on both time-averaged and unsteady flow characteristics.…”

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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Comparison of hot-wire and particle image velocimetry measurements in the zone of interaction of a shock wave with a boundary layer at Mach number of 1.43

2021

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The interaction of a shock wave with a laminar boundary layer was studied at the low supersonic Mach number M = 1.43. The measurements were carried out by particle image velocimetry and hot-wire anemometry. The wide range of Mach numbers in the shear layer occurring in the interaction zone made the analysis of hot-wire anemometer data much more difficult. The paper proposes the method of processing of the hot-wire anemometer data involving the simplified sensor calibration and the data obtained by the particle image velocimetry measurements. Good agreement of the results obtained by two experimental techniques is demonstrated. The data gathered in this work permit simplifying essentially the usage of the hot-wire anemometer technique applied for the study of transonic shear flows.

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Development of disturbances generated by an electric discharge in the shock wave / boundary layer interaction zone

Vishnyakov,

Polivanov,

Sidorenko

et al. 2024

Thermophys. Aeromech.

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On the Problem of Using Particle Image Velocimetry for Measurements in High-Velocity Thin Shear Layers

Cited by 6 publications

References 13 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

Comparison of hot-wire and particle image velocimetry measurements in the zone of interaction of a shock wave with a boundary layer at Mach number of 1.43

Development of disturbances generated by an electric discharge in the shock wave / boundary layer interaction zone

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