Standard

Flow parameters at the supersonic combustor entrance at tests in quasistationary impulse regime. / Akinin, S. A.; Goldfeld, M. A.; Starov, A. V.

19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. ed. / Fomin. Vol. 2027 American Institute of Physics Inc., 2018. 040060 (AIP Conference Proceedings; Vol. 2027).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › Research › peer-review

Harvard

Akinin, SA, Goldfeld, MA & Starov, AV 2018, Flow parameters at the supersonic combustor entrance at tests in quasistationary impulse regime. in Fomin (ed.), 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. vol. 2027, 040060, AIP Conference Proceedings, vol. 2027, American Institute of Physics Inc., 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018, Akademgorodok, Novosibirsk, Russian Federation, 13.08.2018. https://doi.org/10.1063/1.5065334

APA

Akinin, S. A., Goldfeld, M. A., & Starov, A. V. (2018). Flow parameters at the supersonic combustor entrance at tests in quasistationary impulse regime. In Fomin (Ed.), 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018 (Vol. 2027). [040060] (AIP Conference Proceedings; Vol. 2027). American Institute of Physics Inc.. https://doi.org/10.1063/1.5065334

Vancouver

Akinin SA, Goldfeld MA, Starov AV. Flow parameters at the supersonic combustor entrance at tests in quasistationary impulse regime. In Fomin, editor, 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. Vol. 2027. American Institute of Physics Inc. 2018. 040060. (AIP Conference Proceedings). doi: 10.1063/1.5065334

Author

Akinin, S. A. ; Goldfeld, M. A. ; Starov, A. V. / Flow parameters at the supersonic combustor entrance at tests in quasistationary impulse regime. 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. editor / Fomin. Vol. 2027 American Institute of Physics Inc., 2018. (AIP Conference Proceedings).

BibTeX

@inproceedings{bd7d4ef7819846d596157ee18fb03e6d,
title = "Flow parameters at the supersonic combustor entrance at tests in quasistationary impulse regime",
abstract = "The results of the flow investigation at the supersonic combustor entrance at tests in the regime of an attached pipe-line are presented. As a source of working gas, a discharge pre-chamber of an impulse wind tunnel was used. The three-dimensional numerical simulation was performed using the software package ANSYS Fluent from the nozzle critical section to the combustor entrance with experimental initial data. The experiments were carried out with the following airflow parameters: M = 4, total pressure P0 = 5.7÷2.0 MPa and total temperature T0=1750÷1200 K. Air flow characteristics and their distribution at the combustor entrance were obtained. It is established that the Mach number field non-uniformity in the flow core at the combustor entrance is 2.3% with a maximum thickness of the boundary layer of 10.7 mm. A good agreement between the calculated and experimental data was obtained.",
author = "Akinin, {S. A.} and Goldfeld, {M. A.} and Starov, {A. V.}",
note = "Publisher Copyright: {\textcopyright} 2018 Author(s).; 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018 ; Conference date: 13-08-2018 Through 19-08-2018",
year = "2018",
month = nov,
day = "2",
doi = "10.1063/1.5065334",
language = "English",
volume = "2027",
series = "AIP Conference Proceedings",
publisher = "American Institute of Physics Inc.",
editor = "Fomin",
booktitle = "19th International Conference on the Methods of Aerophysical Research, ICMAR 2018",

}

RIS

TY - GEN

T1 - Flow parameters at the supersonic combustor entrance at tests in quasistationary impulse regime

AU - Akinin, S. A.

AU - Goldfeld, M. A.

AU - Starov, A. V.

N1 - Publisher Copyright: © 2018 Author(s).

PY - 2018/11/2

Y1 - 2018/11/2

N2 - The results of the flow investigation at the supersonic combustor entrance at tests in the regime of an attached pipe-line are presented. As a source of working gas, a discharge pre-chamber of an impulse wind tunnel was used. The three-dimensional numerical simulation was performed using the software package ANSYS Fluent from the nozzle critical section to the combustor entrance with experimental initial data. The experiments were carried out with the following airflow parameters: M = 4, total pressure P0 = 5.7÷2.0 MPa and total temperature T0=1750÷1200 K. Air flow characteristics and their distribution at the combustor entrance were obtained. It is established that the Mach number field non-uniformity in the flow core at the combustor entrance is 2.3% with a maximum thickness of the boundary layer of 10.7 mm. A good agreement between the calculated and experimental data was obtained.

AB - The results of the flow investigation at the supersonic combustor entrance at tests in the regime of an attached pipe-line are presented. As a source of working gas, a discharge pre-chamber of an impulse wind tunnel was used. The three-dimensional numerical simulation was performed using the software package ANSYS Fluent from the nozzle critical section to the combustor entrance with experimental initial data. The experiments were carried out with the following airflow parameters: M = 4, total pressure P0 = 5.7÷2.0 MPa and total temperature T0=1750÷1200 K. Air flow characteristics and their distribution at the combustor entrance were obtained. It is established that the Mach number field non-uniformity in the flow core at the combustor entrance is 2.3% with a maximum thickness of the boundary layer of 10.7 mm. A good agreement between the calculated and experimental data was obtained.

UR - http://www.scopus.com/inward/record.url?scp=85056301901&partnerID=8YFLogxK

U2 - 10.1063/1.5065334

DO - 10.1063/1.5065334

M3 - Conference contribution

AN - SCOPUS:85056301901

VL - 2027

T3 - AIP Conference Proceedings

BT - 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018

A2 - Fomin, null

PB - American Institute of Physics Inc.

T2 - 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018

Y2 - 13 August 2018 through 19 August 2018

ER -

ID: 17412012