Airfoil - Critical Reynold?
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. https://t8wcbq-sn3302.files.1drv.com...0R0fQ/Wing.PNG |
Are you asking what Reynolds number boundary layer transition occurs?
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