Aerofoil lift coefficient
Does anybody understand how the OF libforces.so package actually works out the values of lift and drag coefficient?
I'll be more explicit; I'm comparing computational results to experiment and I'm getting a very good approximation for the lift coefficient but not a very good approximation to the pressure distribution on the aerofoil....
I can't understand how this is correct?
I thought it might be something to do with how OpenFOAM works out the actual lift coefficient but from what I understand, openfoam does indeed just integrate the pressure distribution.....
Does anybody have any experience with this and could they point me in the right direction?
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