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.
Import File
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.
...
Define > Models > Solver...
Under the Solver box, select Pressure Based.
Click OK.
Define > Models > Viscous
Select Inviscid under Model.
Click OK.
Define > Models > Energy
...
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.
Click Change/Create.
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.
Click OK.
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.)
Click OK.
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!