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The Design – Basic Flow Simulation Through Perforated Plate | ANSYS Fluent

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In this simulation project, the flow around the perforated plate in three modes of a plate, two plates, and three plates in the same direction in a matched condition has been examined. The effects of the previous plates on the drag coefficient have been studied.

The spacing of the consecutive plates is the same, and the drag coefficients with mesh changes are also investigated.

In this analysis, it has been tried to simulate and analyze the flow of water around the three plates in a continuous manner using Ansys Fluent software.

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The Design – Basic Flow Simulation Through Perforated Plate | ANSYS Fluent

In this simulation project, the flow around the perforated plate in three modes of a plate, two plates, and three plates in the same direction in a matched condition has been examined. The effects of the previous plates on the drag coefficient have been studied.

The spacing of the consecutive plates is the same, and the drag coefficients with mesh changes are also investigated.

In this analysis, it has been tried to simulate and analyze the flow of water around the three plates in a continuous manner using Ansys Fluent software.

Geometry & Grid

The geometry required for this analysis was generated by Ansys Design Modeler software. The meshing required for this analysis was also generated by Ansys Meshing software. The mesh type used in this analysis is unstructured. The total number of volume properties for shell & tube geometry is 3.4862e-003 m³.

The geometry required for this analysis has been generated by Ansys Design Modeler software. For meshing, Ansys Meshing Fluent software has also been used and the mesh type used in this analysis is Inflation, and the total number of nodes produced for this geometry is 18517 nodes.

Model

In this analysis, the k-epsilon Standard turbulence viscosity model has been used to check the fluid flow, and also the Non-Equilibrium Wall Function near the walls has been used.

Boundary Condition

For flow inlet, the velocity-inlet boundary condition is considered at 2 m/s. For the supersonic/initial gauge pressure inlet, the supersonic/initial gauge pressure-inlet boundary condition is considered at 300000 pascals. The outlet is considered a pressure-outlet condition. The flow input for the gauge pressure-outlet solution is 300000 pascal.

Discretization of Equations

Due to the type of heat transfer in this analysis, a Pressure-Based solver has been used to solve the equations and the COUPLE Algorithm for the discretization of velocity and pressure has been used. The energy and momentum equations have been discretized in the second-order upwind.

The results are presented as pressure and velocity contours.

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