In physical engineering, the turbulent flow on the surface roughness is very important. The roughness of the surface changed the distance of the interval. The roughness coefficient occurred with increasing turbulence intensities was stronger. The turbulence intensity away from the roughness in the shape was zero. The variation of turbulence intensity at the experimental flow conditions change was not affected.

In this study, the flow characteristics at the front and the rear side of the diffuser installed in the AHU for Offshore HVAC system were studied. Set up the rectangular prism of which height is H at diffuser inlet duct, the flow control methods were considered using PIV and CFD numerical analysis. Average flow velocity was increased by 37% and the degree of flow uniformity was 96.7% at x/H =1.5.

In this study, we have modeled a subsonic diffuser with rectangular prism and tried to investigate the influence of a turbulent wake flow by numerical simulation using computational fluid dynamics based on steady-state Navier-Stokes equation and standard k-ε model. A commercial CFD program, FLUENT, is used on the analysis. The turbulent wake is generated by a rectangular prism, which is installed at the diffuser. Flow Uniformity Showed the best results in the case of AR=1:1 and tended to be uniform in the critical point at Re=8.8×103

In this study, we have modeled a wide angle diffuser with rectangular prism and tried to investigate the influence of a turbulent wake flow by PIV and a numerical simulation using computational fluid dynamics based on steady-state Navier-Stokes equation and standard k-ε model. A commercial CFD program, FLUENT, is used on the analysis. The turbulent wake is generated by a rectangular prism, which is installed at the diffuser. The results show that it is possible to flow control by installing a rectangular prism within the diffuser and velocity recovery is the highest in aspect ratio 1:1.

Axial flow fan under certain condition may stall. The rise in pressure across the impeller blade of an axial flow fan depends on the angle of attack. At a low back pressure, the air volume will be large and the angle of attack is small. In this study, the time dependent Navier-Stokes equations are numerically solved in large size axial-flow fan with groove