Experimental and Numerical Investigation of a Surface Sliding Discharge in a Supersonic Flow with an Oblique Shock Wave
This study presents an experimental and numerical investigation on a surface sliding discharge in a supersonic airflow in the presence of an oblique shock wave. In experiments, flow Mach numbers were 1.20–1.68 in the shock tube combined with the discharge chamber. A single high-voltage 25 kV pulse s...
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MDPI AG
2022-03-01
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| Series: | Energies |
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| Online Access: | https://www.mdpi.com/1996-1073/15/6/2189 |
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| author | Irina V. Mursenkova Igor E. Ivanov Yugan Liao Igor A. Kryukov |
| author_facet | Irina V. Mursenkova Igor E. Ivanov Yugan Liao Igor A. Kryukov |
| author_sort | Irina V. Mursenkova |
| collection | DOAJ |
| description | This study presents an experimental and numerical investigation on a surface sliding discharge in a supersonic airflow in the presence of an oblique shock wave. In experiments, flow Mach numbers were 1.20–1.68 in the shock tube combined with the discharge chamber. A single high-voltage 25 kV pulse sustains the plasma; the discharge current has a duration of ~500 ns. A surface sliding discharge is developed as a localized channel in a zone of interaction of an oblique shock wave with a boundary layer on the upper wall of the discharge chamber. The discharge channel acts as a linear source of heat and is at the origin of the induced shock wave. The flow field in the discharge chamber is spatio-temporally surveyed using high-speed shadowgraphy imaging with a frequency of up to 525,000 frames per second. The experiments show that the perturbed flow restored the initial structure after more than 100 μs. Numerical simulation with local energy input into the supersonic flow in a flat channel is carried out on the base of unsteady two-dimensional Navier–Stokes equations. It is determined that the dynamics of an induced shock wave are dependent on the energy input regime and on the flow parameters. The thermal energy release in the discharge channel of 0.22–0.29 J was estimated from a comparison of experimental data and numerical simulations. |
| first_indexed | 2024-03-09T13:44:48Z |
| format | Article |
| id | doaj.art-facd9990c4884c0289e1033e2b595df7 |
| institution | Directory Open Access Journal |
| issn | 1996-1073 |
| language | English |
| last_indexed | 2024-03-09T13:44:48Z |
| publishDate | 2022-03-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Energies |
| spelling | doaj.art-facd9990c4884c0289e1033e2b595df72023-11-30T21:02:14ZengMDPI AGEnergies1996-10732022-03-01156218910.3390/en15062189Experimental and Numerical Investigation of a Surface Sliding Discharge in a Supersonic Flow with an Oblique Shock WaveIrina V. Mursenkova0Igor E. Ivanov1Yugan Liao2Igor A. Kryukov3Faculty of Physics, Lomonosov Moscow State University, 119991 Moscow, RussiaFaculty of Physics, Lomonosov Moscow State University, 119991 Moscow, RussiaFaculty of Physics, Lomonosov Moscow State University, 119991 Moscow, RussiaIshlinsky Institute for Problems in Mechanics of the RAS, 119526 Moscow, RussiaThis study presents an experimental and numerical investigation on a surface sliding discharge in a supersonic airflow in the presence of an oblique shock wave. In experiments, flow Mach numbers were 1.20–1.68 in the shock tube combined with the discharge chamber. A single high-voltage 25 kV pulse sustains the plasma; the discharge current has a duration of ~500 ns. A surface sliding discharge is developed as a localized channel in a zone of interaction of an oblique shock wave with a boundary layer on the upper wall of the discharge chamber. The discharge channel acts as a linear source of heat and is at the origin of the induced shock wave. The flow field in the discharge chamber is spatio-temporally surveyed using high-speed shadowgraphy imaging with a frequency of up to 525,000 frames per second. The experiments show that the perturbed flow restored the initial structure after more than 100 μs. Numerical simulation with local energy input into the supersonic flow in a flat channel is carried out on the base of unsteady two-dimensional Navier–Stokes equations. It is determined that the dynamics of an induced shock wave are dependent on the energy input regime and on the flow parameters. The thermal energy release in the discharge channel of 0.22–0.29 J was estimated from a comparison of experimental data and numerical simulations.https://www.mdpi.com/1996-1073/15/6/2189nanosecond surface sliding dischargeplasma actuatorsupersonic flowoblique shock wavehigh-speed shadowgraphynumerical simulation |
| spellingShingle | Irina V. Mursenkova Igor E. Ivanov Yugan Liao Igor A. Kryukov Experimental and Numerical Investigation of a Surface Sliding Discharge in a Supersonic Flow with an Oblique Shock Wave Energies nanosecond surface sliding discharge plasma actuator supersonic flow oblique shock wave high-speed shadowgraphy numerical simulation |
| title | Experimental and Numerical Investigation of a Surface Sliding Discharge in a Supersonic Flow with an Oblique Shock Wave |
| title_full | Experimental and Numerical Investigation of a Surface Sliding Discharge in a Supersonic Flow with an Oblique Shock Wave |
| title_fullStr | Experimental and Numerical Investigation of a Surface Sliding Discharge in a Supersonic Flow with an Oblique Shock Wave |
| title_full_unstemmed | Experimental and Numerical Investigation of a Surface Sliding Discharge in a Supersonic Flow with an Oblique Shock Wave |
| title_short | Experimental and Numerical Investigation of a Surface Sliding Discharge in a Supersonic Flow with an Oblique Shock Wave |
| title_sort | experimental and numerical investigation of a surface sliding discharge in a supersonic flow with an oblique shock wave |
| topic | nanosecond surface sliding discharge plasma actuator supersonic flow oblique shock wave high-speed shadowgraphy numerical simulation |
| url | https://www.mdpi.com/1996-1073/15/6/2189 |
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