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: email@example.com
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
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