Abstract
This paper describes an experimental study of the flow patterns and distribution of heat transfer developed in regions of adverse pressure gradient and separated flow over two-dimensional models in a Mach 10 airflow at a freestream Reynolds number of 1.35 X 10/in. Schlieren photographs and heat-transfer distributions were obtained in regions of adverse pressure gradient and moderately separated flow, induced by both forward-facing wedges and externally generated shock, to detect the difference between a flow in which the boundary layer had been merely thickened by an adverse pressure gradient and one in which there was a region of reverse flow. A separation criterion, based on a distinctive change in heat-transfer profile at the beginning of the interaction, is suggested to distinguish between unseparated and separated flows. A study was made to determine the effect of reattachment angle, boundary-layer thickness at separation, and downstream expansion on the heat transfer generated in the reattachment region on the wedge of a flat-plate-wedge model. The reattachment heat-transfer rates were found to be strongly dependent on reattachment angle; whereas for the configurations tested, there was little influence of the boundary-layer thickness at separation or downstream expansion. The measurements were correlated in terms of the viscous interaction parameters MC# and \R and also compared with calculations based on simple models for the separated flowfield.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have