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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:

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Define > Models > Solver...

Under the Solver box, select Pressure Based.

Click OK.

Define > Models > Viscous

Select Inviscid under Model.

Click OK.

Define > Models > Energy

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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 Methodand 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!