help for Naca 0015 in Gambit & Fluent !!
HI Everybody I used Gambit and Fluent for naca 0015 to find CL at angle of attack 6 deg but the result was wroung and its comes about CL= 0.008 and the correct one is 0.7 and i dont know where the problem is. can anyone help us how to find lift coffiecient for NACA 0015 by using Gambit and Fluent ???? Thank u Rayan |
Are you using Gambit / Fluent or OpenFOAM?
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Naca 0015
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did you define reference values correctly in fluent?
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