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?

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.

regards

Thanks Dmitry.... that did the trick !!