پاورپوینت کامل Introduction to CFX 31 اسلاید در PowerPoint

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پاورپوینت کامل Introduction to CFX 31 اسلاید در PowerPoint

اسلاید ۴: Mesh ModificationOpen CFX-pre by right-clicking on the Setup cell and selecting EditAfter CFX-Pre has opened the mesh can be examined and it is clear that the scale is incorrect as the airfoil chord is 1000 m rather than 1 m, indicating the mesh was built in mm rather than m. This can be fixed using the mesh transformation options.Right-click on Mesh in the Outline tree and select Transform MeshChange the Transformation to ScaleLeave the method to Uniform and enter a Uniform Scale of 0.001Click OKSelect the Fit View icon from the Viewer toolbarZoom in further to see the airfoil

اسلاید ۵: Mesh Modification The mesh has been built to have a single boundary around the entire outer edge. This needs to be split into inlet and outlet regions. While it is better to create the correct mesh regions when generating the mesh, CFX-Pre can be used to modify the mesh regions.Right-click Mesh in the Outline tree and select Insert > Primitive RegionClick on the Start Picking buttonFrom the drop down selection menu select Flood Select (see image to the right)In the viewer select any element from the front curved boundaryThe flood fill will select all cells where the change in angle is less than 30°Click in the Move Faces To field and type InletClick OKInletOutlet

اسلاید ۶: Mesh Modification The remaining section will now be renamed “Outlet”. Expand the Mesh section of the tree so the list of Principal 2D Regions is visible. Note that this list now contains the location InletClick on the region pressure far field 1 to confirm it is the region representing the outletIt will be highlighted in the ViewerRight-click on pressure far field 1 and select Rename. Change the name to Outlet

اسلاید ۷: Domain SetupUsually the option to automatically generate domains is active, this can be checked by editing Case Options > General in the Outline tree.Check that Automatic Default Domain is active the click OK. Right-click on Default Domain in the Outline tree and rename it to FluidDouble-click on Fluid to edit the domain settings

اسلاید ۸: Domain SetupThis case involves high speed aerodynamics so it is important to include compressibility.It is important to set the correct operating pressure so that the intended Reynolds number is achieved. The simulation will take place at 288 [K] in air; this allows the speed of sound to be calculated. This can then be converted into a free-stream velocity using the Mach number. Using the definition for Reynolds number the fluid density can be obtained, which can then be used to determine the operating pressure for the simulation, assuming an ideal gas.c =Speed of soundR=Gas Constant =Ratio of specific heatsT=Temperatureu= Free-stream velocityM=Mach numberRe=Reynolds number= Dynamic viscosity = Density

اسلاید ۹: Domain SetupIn the Fluid domain Basic Settings tab:Set the Material to Air Ideal GasSet the Reference Pressure to 56867 [Pa]Make sure you change set the unitsMove to the Fluid Models tabSet the Heat Transfer Option to Total EnergyThis is required for compressible simulationsEnable Incl. Viscous Work TermThis includes viscous heating effectsSet the Turbulence Option to Shear Stress TransportClick OK

اسلاید ۱۰: Boundary ConditionsAn outlet relative pressure of 0 [Pa] will now be applied. This pressure is relative to the operating pressure of 56867 [Pa].Absolute Pressure = Reference Pressure + Relative PressureRight-click on the domain Fluid in the Outline tree and select Insert > Boundary, naming the boundary OutletChange the Boundary Type to Outlet and check that the location is set to OutletMove to the Boundary Details tab and set the Mass and Momentum option to Average Static Pressure with a value of 0 [Pa]Click OKThe sides of the domain will use symmetry conditions since this is a 2D simulation.Insert a Symmetry boundary called Sym Left, at the location sym leftInsert a Symmetry boundary called Sym Right, at the location sym right

اسلاید ۱۱: Boundary Conditions The mesh has been constructed so that the airfoil is at 0° angle of attack. To apply the required angle of 1.49° the flow direction at the inlet must be adjusted. The values will be created using expressions.Right-click on Expression in the tree and select Insert > Expression. Call it Uinf.Set the Definition to 238.12 [m s^-1] then click ApplyAll expressions must have the appropriate dimensionsIn