DRAG REDUCTION OVER A CIRCULAR CYLINDER

The flow past a circular cylinder has been extensively studied in the past so as to understand the complex flow field acting around the cylinder. The presence of boundary layer separation makes the flow highly unsteady leads to a phenomena of vortex induced vibration which can be highly damaging for cylinder. The major contribution drag on cylinder is due to the pressure drag, it is also observed that the interaction of vortices leads to a higher pressure drag. Therefore the present work aims to restrict the interaction of vortices. The restriction has been bought using a splitter plate fixed at angle Ɵ=180o . Due to the presence of splitter plate, the two vortices in the upper and lower half of the cylinder become blind and do not interact each other. Mainly the present case have been studied with the Effect of length between splitter plate and cylinder. The measurement of surface pressure distribution carried out in the subsonic wind tunnel at a Reynolds's number 35000 and some specified cases of splitter plate with circular cylinder. Results of the present computation were validated present experiments. The pressure distribution along the surface the cylinder, effect splitter plate, strouhal number and time variation of lift and drag were investigated