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On the features of measuring the shock waves parameters under nonuniform flow conditions. / Kiseleva, T. A.

19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. ред. / Fomin. Том 2027 American Institute of Physics Inc., 2018. 030067 (AIP Conference Proceedings; Том 2027).

Результаты исследований: Публикации в книгах, отчётах, сборниках, трудах конференций › статья в сборнике материалов конференции › научная › Рецензирование

Harvard

Kiseleva, TA 2018, On the features of measuring the shock waves parameters under nonuniform flow conditions. в Fomin (ред.), 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. Том. 2027, 030067, AIP Conference Proceedings, Том. 2027, American Institute of Physics Inc., 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018, Akademgorodok, Novosibirsk, Российская Федерация, 13.08.2018. https://doi.org/10.1063/1.5065161

APA

Kiseleva, T. A. (2018). On the features of measuring the shock waves parameters under nonuniform flow conditions. в Fomin (Ред.), 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018 (Том 2027). [030067] (AIP Conference Proceedings; Том 2027). American Institute of Physics Inc.. https://doi.org/10.1063/1.5065161

Vancouver

Kiseleva TA. On the features of measuring the shock waves parameters under nonuniform flow conditions. в Fomin, Редактор, 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. Том 2027. American Institute of Physics Inc. 2018. 030067. (AIP Conference Proceedings). doi: 10.1063/1.5065161

Author

Kiseleva, T. A. / On the features of measuring the shock waves parameters under nonuniform flow conditions. 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. Редактор / Fomin. Том 2027 American Institute of Physics Inc., 2018. (AIP Conference Proceedings).

BibTeX

@inproceedings{5fc8af0548464e4d8f17a872ca7c7bbb,
title = "On the features of measuring the shock waves parameters under nonuniform flow conditions",
abstract = "In the efforts to reduce the intensity of sonic boom generated by a supersonic aircraft, the problem of measuring the parameters of the shock waves in the experiments in a non-uniform flow is considered. It is necessary to measure the static pressure distribution behind the head shock wave at various distances from the model under study. The measured data of the shock wave profile obtained with the help of a drained measuring plate and a comb of pressure probes are given. A technique for processing experimental data is presented.",
author = "Kiseleva, {T. A.}",
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 = "10.1063/1.5065161",
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 - On the features of measuring the shock waves parameters under nonuniform flow conditions

AU - Kiseleva, T. A.

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

PY - 2018/11/2

Y1 - 2018/11/2

N2 - In the efforts to reduce the intensity of sonic boom generated by a supersonic aircraft, the problem of measuring the parameters of the shock waves in the experiments in a non-uniform flow is considered. It is necessary to measure the static pressure distribution behind the head shock wave at various distances from the model under study. The measured data of the shock wave profile obtained with the help of a drained measuring plate and a comb of pressure probes are given. A technique for processing experimental data is presented.

AB - In the efforts to reduce the intensity of sonic boom generated by a supersonic aircraft, the problem of measuring the parameters of the shock waves in the experiments in a non-uniform flow is considered. It is necessary to measure the static pressure distribution behind the head shock wave at various distances from the model under study. The measured data of the shock wave profile obtained with the help of a drained measuring plate and a comb of pressure probes are given. A technique for processing experimental data is presented.

UR - http://www.scopus.com/inward/record.url?scp=85056298165&partnerID=8YFLogxK

U2 - 10.1063/1.5065161

DO - 10.1063/1.5065161

M3 - Conference contribution

AN - SCOPUS:85056298165

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: 17413338