$FOAM_TUTORIALS/incompressible/simpleFoam/airFoil2D

We calculate the steady flow around a 2-dimensional airfoil using a prepared mesh.

The region "inlet" and "outlet" are set to fixed values (25.75, 3.62, 0) m/s and the boundary condition "freestream" is set. The freestream condition switches between the fixed value and zero gradient depending on the flow direction. The airfoil surface (region "wall") is set to the no-slip wall condition. The problem is solved as a 2-dimensional problem with a single mesh in Z-direction.

The flow velocity (25.75, 3.62, 0) m/s is set as the initial condition.

The turbulence model is the Spalart-Allmaras model.

Model geometry

The meshes are as follows, and the number of mesh is 10720.

Mesh (entire)

Mesh (around a airfoil)

The calculation result is as follows.

Flow velocity (U)

Pressure (p)

cp -r $FOAM_TUTORIALS/incompressible/simpleFoam/airFoil2D airFoil2D

cd airFoil2D

simpleFoam

paraFoam

cd airFoil2D

simpleFoam

paraFoam

The mesh is already prepared, so we will only run the solver.

9.7 seconds *Single, Inter(R) Core(TM) i7-2600 CPU @ 3.40GHz 3.40GHz