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January 26, 2016, 07:48 |
wrong Aerodynamic coefficient
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#1 |
New Member
Marcello
Join Date: Jul 2015
Posts: 3
Rep Power: 10 |
Hello guys,
i'm doing a work on a NACA 4415 with simpleFoam solver and i have some trouble with Cd that's a lot higher than expected (0.015 vs 0.008). here's the link of the mesh https://picasaweb.google.com/1086153...75949717864098 i'm using bounded Gauss upwind for U, k, eps U inlet 50 Re = 3e6 and the ControlDict Code:
forceCoeffs { type forceCoeffs; functionObjectLibs ( "libforces.so" ); outputControl timeStep; outputInterval 1; patches ( profile ); pName p; UName U; rhoName rhoInf; log true; rhoInf 1.16; CofR ( 0 0 0 ); liftDir ( 0 1 0 ); dragDir ( 1 0 0 ); pitchAxis ( 0 0 1 ); magUInf 50; lRef 1; Aref 1; //lRef 0.55; //Aref 0.0825; } Thank you all, Marcello |
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