viscous term in energy equation
I am using rhoSimpleFoam on a fuselage at Mach 0.78.
I had a look at the energy equation and the term involving the viscous
stresses is not implemented. Looking at the openFOAM results, the static temperature decreases slightly as we go to the wall whereas in the reference calculation I have, it increases.
Does anyone know above which Mach number this viscous term becomes influencial, and if an openFOAM solver takes it into account?
Thanks a lot
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