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Old   January 10, 2003, 07:49
Default negative drag coeffient
mehdi icho
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hello every one

I am studying a supercritical airfoil with fluent. and for mach 0.5 flow I obtained a negative drag coefficient, this ic completely wrong. I used the same way of meshing and defining boundary conditions as in the tutorial. I only change the airfoil. do you know how can I face this problem?

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