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January 10, 2003, 06:49
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negative drag coeffient
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Guest
Posts: n/a
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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? thanks |
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