Adiabatic wall temperature and heat transfer coefficient influenced by separated supersonic flow

Adiabatic wall temperature and heat transfer coefficient influenced by separated supersonic flow

Investigations of supersonic air flow around plane surface behind a rib perpendicular to the flow direction are performed. Research was carried out for free stream Mach number 2.25 and turbulent flow regime - Rex>2·107. Rib height was varied in range from 2 to 8 mm while boundary layer thickness...

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Bibliographic Details
Main Authors: Leontiev Alexander, Popovich Sergey, Strongin Mark, Vinogradov Yurii
Format: Article
Language:English
Published: EDP Sciences 2017-01-01
Series:EPJ Web of Conferences
Online Access:https://doi.org/10.1051/epjconf/201715900030
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spelling doaj-1176c89621ce473988803ef6ca58e5322021-08-02T18:30:33ZengEDP SciencesEPJ Web of Conferences2100-014X2017-01-011590003010.1051/epjconf/201715900030epjconf_avtfg2017_00030Adiabatic wall temperature and heat transfer coefficient influenced by separated supersonic flowLeontiev AlexanderPopovich SergeyStrongin MarkVinogradov YuriiInvestigations of supersonic air flow around plane surface behind a rib perpendicular to the flow direction are performed. Research was carried out for free stream Mach number 2.25 and turbulent flow regime - Rex>2·107. Rib height was varied in range from 2 to 8 mm while boundary layer thickness at the nozzle exit section was about 6 mm. As a result adiabatic wall temperature and heat transfer coefficient are obtained for flow around plane surface behind a rib incontrast with the flow around plane surface without any disturbances.https://doi.org/10.1051/epjconf/201715900030
collection DOAJ
language English
format Article
sources DOAJ
author Leontiev Alexander
Popovich Sergey
Strongin Mark
Vinogradov Yurii
spellingShingle Leontiev Alexander
Popovich Sergey
Strongin Mark
Vinogradov Yurii
Adiabatic wall temperature and heat transfer coefficient influenced by separated supersonic flow
EPJ Web of Conferences
author_facet Leontiev Alexander
Popovich Sergey
Strongin Mark
Vinogradov Yurii
author_sort Leontiev Alexander
title Adiabatic wall temperature and heat transfer coefficient influenced by separated supersonic flow
title_short Adiabatic wall temperature and heat transfer coefficient influenced by separated supersonic flow
title_full Adiabatic wall temperature and heat transfer coefficient influenced by separated supersonic flow
title_fullStr Adiabatic wall temperature and heat transfer coefficient influenced by separated supersonic flow
title_full_unstemmed Adiabatic wall temperature and heat transfer coefficient influenced by separated supersonic flow
title_sort adiabatic wall temperature and heat transfer coefficient influenced by separated supersonic flow
publisher EDP Sciences
series EPJ Web of Conferences
issn 2100-014X
publishDate 2017-01-01
description Investigations of supersonic air flow around plane surface behind a rib perpendicular to the flow direction are performed. Research was carried out for free stream Mach number 2.25 and turbulent flow regime - Rex>2·107. Rib height was varied in range from 2 to 8 mm while boundary layer thickness at the nozzle exit section was about 6 mm. As a result adiabatic wall temperature and heat transfer coefficient are obtained for flow around plane surface behind a rib incontrast with the flow around plane surface without any disturbances.
url https://doi.org/10.1051/epjconf/201715900030
work_keys_str_mv AT leontievalexander adiabaticwalltemperatureandheattransfercoefficientinfluencedbyseparatedsupersonicflow
AT popovichsergey adiabaticwalltemperatureandheattransfercoefficientinfluencedbyseparatedsupersonicflow
AT stronginmark adiabaticwalltemperatureandheattransfercoefficientinfluencedbyseparatedsupersonicflow
AT vinogradovyurii adiabaticwalltemperatureandheattransfercoefficientinfluencedbyseparatedsupersonicflow
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