Abstract
An experimental campaign over a compression corner in a Mach 6 hypersonic flow was conducted to investigate the performance of a differential Reynolds stress model (RSM). Two compression angles have been chosen in order to obtain an attached flow (15-degrees) and a separated flow (40-degrees). The numerical results obtained using the RSM were compared with the numerical findings and with the results from standard linear eddy viscosity models and an explicit algebraic Reynolds stress model. As expected, all models performed similarly for the 15-degrees case in terms of wall pressure and heat flux while appreciable differences were visible at 40-degrees when the boundary layer separates. In this case the Reynlds stress based models proved to be superior to the eddy viscosity ones.
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