• Proceedings of the KSME Conference
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• 2007.05b
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• pp.2567-2572
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• 2007

The suppression of fluid force acting on a square prism near plane wall was studied by attaching fences on the corners of the prism. The height of the fence was 10% of the square width and the range of Reynolds number considered was Re=$2.0{\times}10^4$. The experimental parameters were the attaching position and numbers of fences, the space ratios G/B(G/B=0.1${\sim}$1.2) between prism and plane wall. The average drag coefficients were increased and the average lift coefficients were decreased and increased with the space ratios toward plane wall. The drag of the prism was reduced average 7.6% with the space ratios by attaching the normal fence at the rear and upper corner and the horizontal normal fence at the rear and lower corner on the prism. In this case, the separated flow at the front and upper corner was reattached on the upper side of the prism and the vortex streets between the prism and plane wall were appeared more slowly than that of prism without fences.

• Proceedings of the Korean Society of Marine Engineers Conference
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• 2006.06a
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• pp.61-62
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• 2006

The suppression of fluid force acting on a square prism near plane wall was studied by attaching fences on the comers of the prism. The height of the fence was 10% of the square width and the range of Reynolds number considered was $Re=2.0{\times}10^4$. The experimental parameters were the attaching position and numbers of fences, the space ratios $G/B(G/B=0.1{\sim}1.2)$ between prism and plane wall. The average drag coefficients were increased and the average hit coefficients were decreased and increased with the space ratios foulard plane wall. The drag of the prism was reduced average 7.6% with the space ratios by attaching the normal fence at the rear and upper comer and the horizontal normal fence at the rear and lower corner on the prism.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.59-63
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• 2005

The experimental study has been conducted to investigate the effect of the recirculation zone on the multi-slot film cooling in the ramjet combustor. The recirculation zone which is generated by the protrusion tip on the entrance of the coolant flow path affects on the first slot. Velocity fields, dimensionless temperature fields and adiabatic film cooling effectiveness on the downstream wall of the slot exit are measured. The results show that the film cooling performance is rapidly decreased after the slot exit by the share layer and high turbulence intensity between separated flows and coolant flows.