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aerodynamic characteristic of NACA0012

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Old   June 7, 2008, 00:50
Default aerodynamic characteristic of NACA0012
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I am new to Fluent. I am working on the NACA 0012 Airfoil. i am trying to match the coputed results with the experimental dat. i get very different drag coeff. whereas lift coefficient is good. i have computed this with invisid flow, and PRESTo for pressure under discretization. for this condition i get highr stall angle like 2o deg. but when i use second order for pressure under discretization... i get slightly lower lift coefficient witrhin 10% and getr stalling angle as 14 deg. can anybody explain me. i would like to know. what is the best way to get the experimental data matched
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