Solving Inviscid Compressible Flow
 

Hi all,

I am just started using OpenFoam and trying to solve Inviscid compressible flow around NACA0012 airfoil for Mach No=0.5 & alpha - 0.

If i give "slip" boundary condition for airfoil, it will be treated as Inviscid wall and OpenFoam solves only Euler equation? please clarify

Hi someone please reply..

someone reply please...

:confused:

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A good place to start is the rhoCentralFoam solver. This solves the Euler equations for compressible flow.

Take a look at the tutorial cases (LadenburgJet60psi for example) for details of how to apply the wall boundary conditions.