Choice of boundary conditions at the unsteady modeling of jets flowing into the supersonic flow

V. P. Zamuraev; A. P. Kalinina; D. S. Popova; D. V. Fedorova; O. N. Ivanova

doi:10.1088/1742-6596/1268/1/012024

Choice of boundary conditions at the unsteady modeling of jets flowing into the supersonic flow

V. P. Zamuraev, A. P. Kalinina, D. S. Popova, D. V. Fedorova, O. N. Ivanova

Результат исследования: Научные публикации в периодических изданиях › статья по материалам конференции › рецензирование

3 Цитирования (Scopus)

Аннотация

Numerical simulation of ignition of the gas mixture not mixed previously in the supersonic flow localized in a channel was performed. The ignition is initiated by the shock wave from the throttling jet, which results in significant changing of pressure difference between the main flow and the gas generator of the throttling jet. It is shown that applying boundary conditions similar to the breakdown of arbitrary discontinuity conditions, makes it possible to obtain the transonic mode observed in the experiment. The near-wall and axisymmetric supply of the gaseous fuel was considered.

Язык оригинала	английский
Номер статьи	012024
Число страниц	6
Журнал	Journal of Physics: Conference Series
Том	1268
Номер выпуска	1
DOI	https://doi.org/10.1088/1742-6596/1268/1/012024
Состояние	Опубликовано - 16 июл. 2019
Событие	All-Russian Conference and School for Young Scientists, devoted to 100th Anniversary of Academician L.V. Ovsiannikov on Mathematical Problems of Continuum Mechanics, MPCM 2019 - Novosibirsk, Российская Федерация Продолжительность: 13 мая 2019 → 17 мая 2019

Доступ к документу

10.1088/1742-6596/1268/1/012024

Другие файлы и ссылки

Link to publication in Scopus

Fingerprint

Подробные сведения о темах исследования «Choice of boundary conditions at the unsteady modeling of jets flowing into the supersonic flow». Вместе они формируют уникальный семантический отпечаток (fingerprint).

Цитировать

@article{d993c7b8a209423b8cc4a5855c34b2ca,

title = "Choice of boundary conditions at the unsteady modeling of jets flowing into the supersonic flow",

abstract = "Numerical simulation of ignition of the gas mixture not mixed previously in the supersonic flow localized in a channel was performed. The ignition is initiated by the shock wave from the throttling jet, which results in significant changing of pressure difference between the main flow and the gas generator of the throttling jet. It is shown that applying boundary conditions similar to the breakdown of arbitrary discontinuity conditions, makes it possible to obtain the transonic mode observed in the experiment. The near-wall and axisymmetric supply of the gaseous fuel was considered.",

author = "Zamuraev, {V. P.} and Kalinina, {A. P.} and Popova, {D. S.} and Fedorova, {D. V.} and Ivanova, {O. N.}",

year = "2019",

month = jul,

day = "16",

doi = "10.1088/1742-6596/1268/1/012024",

language = "English",

volume = "1268",

journal = "Journal of Physics: Conference Series",

issn = "1742-6588",

publisher = "IOP Publishing Ltd.",

number = "1",

note = "All-Russian Conference and School for Young Scientists, devoted to 100th Anniversary of Academician L.V. Ovsiannikov on Mathematical Problems of Continuum Mechanics, MPCM 2019 ; Conference date: 13-05-2019 Through 17-05-2019",

}

Choice of boundary conditions at the unsteady modeling of jets flowing into the supersonic flow. / Zamuraev, V. P.; Kalinina, A. P.; Popova, D. S. и др.

В: Journal of Physics: Conference Series, Том 1268, № 1, 012024, 16.07.2019.

Результат исследования: Научные публикации в периодических изданиях › статья по материалам конференции › рецензирование

TY - JOUR

T1 - Choice of boundary conditions at the unsteady modeling of jets flowing into the supersonic flow

AU - Zamuraev, V. P.

AU - Kalinina, A. P.

AU - Popova, D. S.

AU - Fedorova, D. V.

AU - Ivanova, O. N.

PY - 2019/7/16

Y1 - 2019/7/16

N2 - Numerical simulation of ignition of the gas mixture not mixed previously in the supersonic flow localized in a channel was performed. The ignition is initiated by the shock wave from the throttling jet, which results in significant changing of pressure difference between the main flow and the gas generator of the throttling jet. It is shown that applying boundary conditions similar to the breakdown of arbitrary discontinuity conditions, makes it possible to obtain the transonic mode observed in the experiment. The near-wall and axisymmetric supply of the gaseous fuel was considered.

AB - Numerical simulation of ignition of the gas mixture not mixed previously in the supersonic flow localized in a channel was performed. The ignition is initiated by the shock wave from the throttling jet, which results in significant changing of pressure difference between the main flow and the gas generator of the throttling jet. It is shown that applying boundary conditions similar to the breakdown of arbitrary discontinuity conditions, makes it possible to obtain the transonic mode observed in the experiment. The near-wall and axisymmetric supply of the gaseous fuel was considered.

UR - http://www.scopus.com/inward/record.url?scp=85073900752&partnerID=8YFLogxK

U2 - 10.1088/1742-6596/1268/1/012024

DO - 10.1088/1742-6596/1268/1/012024

M3 - Conference article

AN - SCOPUS:85073900752

VL - 1268

JO - Journal of Physics: Conference Series

JF - Journal of Physics: Conference Series

SN - 1742-6588

IS - 1

M1 - 012024

T2 - All-Russian Conference and School for Young Scientists, devoted to 100th Anniversary of Academician L.V. Ovsiannikov on Mathematical Problems of Continuum Mechanics, MPCM 2019

Y2 - 13 May 2019 through 17 May 2019

ER -