https://doi.org/10.1051/epjconf/201715900030
Adiabatic wall temperature and heat transfer coefficient influenced by separated supersonic flow
Institute of Mechanics, Lomonosov Moscow State University,1, Michurinsky Pr., Moscow, 119192, Russia
* Corresponding author: pss1@mail.ru
Published online: 25 October 2017
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.
© The authors, published by EDP Sciences, 2017
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (http://creativecommons.org/licenses/by/4.0/).
