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

Alexander Leontiev, Sergey Popovich, Mark Strongin, Yurii Vinogradov, D. Markovich, D. Zaitsev, A. Semenov
2017 EPJ Web of Conferences  
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>2·10 7 . 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 in contrast with the flow around
more » ... th the flow around plane surface without any disturbances.
doi:10.1051/epjconf/201715900030 fatcat:piefurapmbefneliw5nyli7mby