Abstract: The objective of the present study is to investigate the characteristics of a flow around a rotating circular cylinder with and without an end plate near a wall boundary. The different cases which are taken into consideration in the current investigations were with gap ratios of 0.1d, 0.5d, 1.0d, 1.5d and 2.0d. A symmetric end plate is attached behind the rotating circular cylinder at a distance of 0.1d from the cylinder and a gap ratio of 1.5d. We performed Computational Fluid Dynamics (CFD) simulation of the flow around a rotating circular cylinder near a plane wall boundary using a CFD solver, STAR-CCM+. Free-stream velocity is kept constant at 5 m/s and the Reynolds number calculated is 3.24X10 4 . We then studied the flow characteristics such as lift and drag generated on the circular cylinder with and without an end plate and the wake structure. We observed that the vortex suppression is increased when the gap ratio is reduced, i.e., when the circular cylinder is nearer to the plane wall boundary. As the gap ratio increases the drag force generated decreases and the lift force increases considerably. In the case of rotating circular cylinder with an end plate, the wake area has moved upwards and the lift generated has increased manifold.

This text offers an authoritative compilation of experimental data, theoretical models, and computer simulations which will provide the reader with a comprehensive survey of research work on the phenomenon of flow around circular cylinders.

The flow configurations around and the forces acting on a circular cylinder with its axis parallel to a nearby plane boundary and subjected to a uniform flow were investigated. The flow conditions, which were perpendicular to the cylinder axis and parallel to the plane boundary were investigated experimentally and theoretically. Flow visualization was achieved through the use of tiny air bubbles entrapted in the fluid to locate the stagnation point and point of separation of flow. Also, the configuration of the cylinder wake was observed. A force measuring device employing the use of straingauges was used to record the change in lift and drag as the cylinder neared the plane boundary. The results showed that the drag and lift increased, and that the cylinder wake approximated that of an aerofoil configuration as the cylinder neared the plane boundary. In addition, as the cylinder approached the plane boundary, the top separation point of the cylinder boundary layer moved towards the front of the cylinder, the bottom separation point moved towards the rear of the cylinder, and the front stagnation point moved downward. The boundary layer along the plane boundary was observed to separate at a position downstream of the test cylinder. This separation point position was determined to be a function of the distance between the cylinder and the plane boundary for a specific Reynolds number.