Tut 3 in fluent..
I was trying to solve compressible flow over a Naca 0012 airfoil in the way similar to that in tutorail 3. The problem that I get is that my reynolds number should be 10,000 and my mach number shld be only 0.4.
I can change the mach number directly to 0.4 but I donno know how he calculates the reynolds for that case. what is the formula for calculation reynolds number for this case.
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