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Filtra

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Turbulent Flow Over an Airfoil

Posted 7 dic 2011, 12:59 GMT-5 Computational Fluid Dynamics (CFD) Version 4.2a 0 Replies

Sam Newbauer
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Hi,

I am modeling an airfoil and am trying to calculate the lift and drag coefficients, however the reacf() function returns a 0 value (a parametric sweep was done varying the angle of attack, so the lift and drag force shouldn't be zero at all angles of attack). Is there another command that can calculate the forces on the airfoil?

Thanks,

Sam
0 Replies Last Post 7 dic 2011, 12:59 GMT-5
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