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Air foil, drag coefficient

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Old   April 14, 2004, 17:33
Default Air foil, drag coefficient
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I am trying to model an airfoil using k-epsilion model (standard wall treatment). Inlet air velocity is 100 m/s with 12 degree angle of attack. I get unusually large values for drag and lift coefficients (approx. 6000). What am I doing wrong?
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Old   April 15, 2004, 00:21
Default Re: Air foil, drag coefficient
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Hi, as you know Cx = X/D, where D = 1/2*rho*U^2*A, rho - density, U - velocity, A - area, X - force. FLUENT uses values which are specified in FLUENT reference panel (in FLUENT menu: report->reference values) by default. I think you must set correct values for density, velocity and area there.

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Old   April 16, 2004, 00:40
Default Re: Air foil, drag coefficient
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Thanks Dmitry.... that did the trick !!
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