2020
DOI: 10.3103/s1052618820010082
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Flat-Probe Diagnostic Methods for Collisional Plasma Flowing from Technological Plasmatrons

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Cited by 1 publication
(2 citation statements)
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“…[4][5] The block structure and the number of grid elements along each of block sides to calculate the jet without a diffuser is shown in We calculated the flow in ANSYS CFX by control volume analysis using the compressible ideal gas model, enthalpy complete equation to calculate thermal transfer concerning variable density, and k-ε turbulence model. [6][7][8] Given the jet inlet temperature equal to 10 700 К, the air velocity at inlet being 770 m/s, is lower than the sound speed (Mach number 0,3-0,4), that is why we chose the subsonic condition of jet inlet ( Figure Figure 10). [7] The area around the jet is considered as an adiabatic wall.…”
Section: Methodsmentioning
confidence: 99%
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“…[4][5] The block structure and the number of grid elements along each of block sides to calculate the jet without a diffuser is shown in We calculated the flow in ANSYS CFX by control volume analysis using the compressible ideal gas model, enthalpy complete equation to calculate thermal transfer concerning variable density, and k-ε turbulence model. [6][7][8] Given the jet inlet temperature equal to 10 700 К, the air velocity at inlet being 770 m/s, is lower than the sound speed (Mach number 0,3-0,4), that is why we chose the subsonic condition of jet inlet ( Figure Figure 10). [7] The area around the jet is considered as an adiabatic wall.…”
Section: Methodsmentioning
confidence: 99%
“…[6][7][8] Given the jet inlet temperature equal to 10 700 К, the air velocity at inlet being 770 m/s, is lower than the sound speed (Mach number 0,3-0,4), that is why we chose the subsonic condition of jet inlet ( Figure Figure 10). [7] The area around the jet is considered as an adiabatic wall. We define other borders by ambient pressure equal to 1 atm and 20 °С.…”
Section: Methodsmentioning
confidence: 99%