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March 10, 2015, 08:39
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Too low Cl values
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New Member
nir modan
Join Date: Mar 2015
Posts: 1
Rep Power: 0  |
hello everyone!
I'm new at Fluent and CFD in general. I'm trying to get lift and drag coefficients of NACA4412. Whatever i try to do or change, mesh, BC, etc, i don't get even a close result for values i found on airfoiltools.com. for exemple, at AoA of 10 deg i suppose to achieve Cl=1.3 while the closest result i get is Cl=0.4. Re=1e6 c=0.3 Viscosity model ->K-omega SST on the Cl monitor i tried to defined a vector (-sin(10),cos(10)). Thanks, Nir |
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