Mesh quality all check out. Attached is a zoomed out picture of the mesh. This is has 7 million cells with y+ around 200. As described above reference values are as follows:
Area: planform area of aircraft, Density: fluent calculated via pressure farfield BC, Enthalpy: pressure farfield, Length: from aircraft geometry, Pressure: this is static pressure from the pressure farfield calculated from atmosphere tables, Temperature: pressure farfield, Velocity: pressure farfeild, Ratio of Specific heat: default, yplus for heat transfer: default.
Any thoughts on that reference values or the mesh? I realize the mesh isn't perfect but it should be good enough to at least be within an order of magnitude right? Regarding the NACA airfoil help where is that located?
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