Given Mach number (Fixed), angle of attack, chord length (1m), Reynolds number, I have modeled the flow of air around an airfoil using the Spalart-Allmaras model. I used the FLUENT tutorial, there is no way to input the Reynolds Number directly. How do I obtain the Reynolds number, and how do I vary the Reynolds number? I know Re = (U*L*rho)/mu, I used farfeild in the "Compute From" of the Reference Values. Should I just substitute with the numbers given there to obtain Reynolds Number?

Hello,

As you have written, you can change the density and/or viscosity. (If Mach no was not a concern, you could change the velocity and could still work with air)

greetings.

[Amit soni]

But U is not matching when i calculated with M and Re