|March 2, 2010, 09:56||
Solving Inviscid Compressible Flow
Join Date: Oct 2009
Location: Chennai, India
Posts: 102Rep Power: 9
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
|March 5, 2010, 13:47||
Join Date: Mar 2009
Location: Bournemouth, UK
Posts: 25Rep Power: 9
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.
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