[Wingman]

Hi,

I am trying to choose the most appropriate model for my airfoil / wing. The chord length is approximately 0.165m and my maximum velocity of 15 m/s. I'm using density of 1.225 kg/m3 and dynamic viscosity of 0.000018375 kg/ms.

Using Re = (rho*V*L)/(mu) = (1.225*15*0.165)/(0.000018375)
gives me Reynolds number of 165.000.

What is the Critical Reynolds number for Airfoils? Is there some rule of thumb for this? I'm leaning towards a Turbulent model... k-omega SST?

The wing I'm using has different shape than most NACA profiles and has a blunt edge.

[fluid23]

Are you asking what Reynolds number boundary layer transition occurs?

[truffaldino]

Originally Posted by Wingman

What is the Critical Reynolds number for Airfoils? Is there some rule of thumb for this? I'm leaning towards a Turbulent model... k-omega SST?

The wing I'm using has different shape than most NACA profiles and has a blunt edge.

You will be wasting your tme with k-omega and any other turbulence modelling at such a low reynolds number. Use x-foil or xflr5: if there is no massive separation/bubbles, then your results will be much more accurate and you will easily and quickly see if there is separation, transition, where it happens etc.