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Non-uniqueness of transonic flow in an intake-type channel. / Kuzmin, A.

в: Journal of Physics: Conference Series, Том 1392, № 1, 012012, 13.12.2019.

Результаты исследований: Научные публикации в периодических изданиях › статья в журнале по материалам конференции › Рецензирование

Harvard

Kuzmin, A 2019, 'Non-uniqueness of transonic flow in an intake-type channel', Journal of Physics: Conference Series, Том. 1392, № 1, 012012. https://doi.org/10.1088/1742-6596/1392/1/012012

APA

Kuzmin, A. (2019). Non-uniqueness of transonic flow in an intake-type channel. Journal of Physics: Conference Series, 1392(1), [012012]. https://doi.org/10.1088/1742-6596/1392/1/012012

Vancouver

Kuzmin A. Non-uniqueness of transonic flow in an intake-type channel. Journal of Physics: Conference Series. 2019 Дек. 13;1392(1). 012012. https://doi.org/10.1088/1742-6596/1392/1/012012

Author

Kuzmin, A. / Non-uniqueness of transonic flow in an intake-type channel. в: Journal of Physics: Conference Series. 2019 ; Том 1392, № 1.

BibTeX

@article{cfb97ba4dc48423086e9f272cc7f0838,
title = "Non-uniqueness of transonic flow in an intake-type channel",
abstract = "The two-dimensional turbulent airflow in a 9-degrees-bent channel is studied numerically. Inner surfaces of the top and bottom walls are parallel to each other upstream and downstream of the bend. The free stream is supersonic, whereas the flow is subsonic at the channel exit. Solutions of the Reynolds-averaged Navier-Stokes equations are obtained with a finite-volume solver using the Spalart-Allmaras and Shear Stress Transport k-! turbulence models. The solutions reveal a flow hysteresis and non-uniqueness in considerable bands of the free-stream Mach number, angle of attack, and exit pressure. At the endpoints of the bands, there are abrupt changes of the shock wave system. The non-uniqueness admits different losses of the total pressure, which may cause different trusts of an air breathing engine.",
author = "A. Kuzmin",
year = "2019",
month = dec,
day = "13",
doi = "10.1088/1742-6596/1392/1/012012",
language = "English",
volume = "1392",
journal = "Journal of Physics: Conference Series",
issn = "1742-6588",
publisher = "IOP Publishing Ltd.",
number = "1",
note = "4th International Conference on Supercomputer Technologies of Mathematical Modelling, SCTeMM 2019 ; Conference date: 19-06-2019 Through 21-06-2019",

}

RIS

TY - JOUR

T1 - Non-uniqueness of transonic flow in an intake-type channel

AU - Kuzmin, A.

PY - 2019/12/13

Y1 - 2019/12/13

N2 - The two-dimensional turbulent airflow in a 9-degrees-bent channel is studied numerically. Inner surfaces of the top and bottom walls are parallel to each other upstream and downstream of the bend. The free stream is supersonic, whereas the flow is subsonic at the channel exit. Solutions of the Reynolds-averaged Navier-Stokes equations are obtained with a finite-volume solver using the Spalart-Allmaras and Shear Stress Transport k-! turbulence models. The solutions reveal a flow hysteresis and non-uniqueness in considerable bands of the free-stream Mach number, angle of attack, and exit pressure. At the endpoints of the bands, there are abrupt changes of the shock wave system. The non-uniqueness admits different losses of the total pressure, which may cause different trusts of an air breathing engine.

AB - The two-dimensional turbulent airflow in a 9-degrees-bent channel is studied numerically. Inner surfaces of the top and bottom walls are parallel to each other upstream and downstream of the bend. The free stream is supersonic, whereas the flow is subsonic at the channel exit. Solutions of the Reynolds-averaged Navier-Stokes equations are obtained with a finite-volume solver using the Spalart-Allmaras and Shear Stress Transport k-! turbulence models. The solutions reveal a flow hysteresis and non-uniqueness in considerable bands of the free-stream Mach number, angle of attack, and exit pressure. At the endpoints of the bands, there are abrupt changes of the shock wave system. The non-uniqueness admits different losses of the total pressure, which may cause different trusts of an air breathing engine.

UR - http://www.scopus.com/inward/record.url?scp=85078099478&partnerID=8YFLogxK

U2 - 10.1088/1742-6596/1392/1/012012

DO - 10.1088/1742-6596/1392/1/012012

M3 - Conference article

AN - SCOPUS:85078099478

VL - 1392

JO - Journal of Physics: Conference Series

JF - Journal of Physics: Conference Series

SN - 1742-6588

IS - 1

M1 - 012012

T2 - 4th International Conference on Supercomputer Technologies of Mathematical Modelling, SCTeMM 2019

Y2 - 19 June 2019 through 21 June 2019

ER -

ID: 50476505