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December 12, 2006, 06:36 |
airfoil: drag and lift coefficients
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#1 |
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hi evereybody
I want to calculate the drag coefficient and lift coefficient on an airfoil (2d wing).When I go to Report>>Forces it shows the pressure coeficcient, total force and pressure force, which is something that I don't need. Also if i request to calculate the area of the wing it gives 0.20426972m2.On the reference values the area is 1.If I change the are here doesn't do anything... What should I do? |
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