Step 4: Set Up Problem in FLUENT
Start > Programs > Fluent Inc > FLUENT 6.3.26
Select 2ddp from the list of options and click Run.
Main Menu > File > Read > Case...
Navigate to your working directory and select the
airfoil.msh file. Click OK.
The following should appear in the FLUENT window:
Check that the displayed information is consistent with our expectations of the airfoil grid.
Grid > Info > Size
How many cells and nodes does the grid have?
Display > Grid
Note what the surfaces farfield1, farfield2, etc. correspond to by selecting and plotting them in turn.
Zoom into the airfoil.
Where are the nodes clustered? Why?
Define > Models > Solver...
Under the Solver box, select Pressure Based.
Define > Models > Viscous
Select Inviscid under Model.
Define > Models > Energy
The speed of sound under SSL conditions is 340 m/s so that our freestream Mach number is around 0.15. This is low enough that we'll assume that the flow is incompressible. So the energy equation can be turned off.
Make sure there is no check in the box next to Energy Equation and click OK.
Define > Materials
Make sure air is selected under Fluid Materials. Set Density to constant and equal to 1.225 kg/m3.
Define > Operating Conditions
We'll work in terms of gauge pressures in this example. So set Operating Pressure to the ambient value of 101,325 Pa.
Define > Boundary Conditions
Set farfield1 and farfield2 to the velocity-inlet boundary type.
For each, click Set.... Then, choose Components under Velocity Specification Method and set the x- and y-components to that for the freestream. For instance, the x-component is 50*cos(1.2)=49.99. (Note that 1.2° is used as our angle of attack instead of 2° to adjust for the error caused by assuming the airfoil to be 2D instead of 3D.)
Set farfield3 to pressure-outlet boundary type, click Set... and set the Gauge Pressure at this boundary to 0. Click OK.
Go to Step 5: Solve!
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