Airfoil "Near Leading Edge" Heat Transfer question
Colleagues... I have a Y+~1 mesh (with associated near-wall mesh spreading), running with the K-omega SST turbulence modeling. The analysis runs around an airfoil section. The approaching flowpath is turbulent (Intensity ~ 5%, dissipation lengh specified), compressible flow. Since I have a refined wall mesh, the boundary layer (BL) is integrated to the wall through the mesh, and heat flux = K*dT/dY at the wall. Near the airfoil leading edge region, does CFX return a heat flux (and HTC)result indicative of the newly forming (ie: laminar boundary layer) with some freestream turbulence influences...or is the heat flux indicative of a turbulent (post-transitional)boundary bayer? Thank you for your insights. Glenn
Re: Airfoil "Near Leading Edge" Heat Transfer ques
To model the laminar to turbulent transition and associated heat transfer effects you will need to turn the turbulence transition model on. If you have not got it on the model assumes the flow is turbulent everywhere.
Regards, Glenn Horrocks
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