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problem numerical results of lift and drag in airfoil simulation using fluent solver |
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June 7, 2018, 03:59
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problem numerical results of lift and drag in airfoil simulation using fluent solver
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New Member
Mohammmad ali gheidi shahran
Join Date: Jul 2017
Location: Tehran
Posts: 6
Rep Power: 10  |
hello everyone,
i have a problem in validation the test results( numerical and experimantal) when i using fluent solver in 2d NACA 4412 airfoil simulation. in zero AOA error of CL is 7.5% and CD is 12%. i want to reduce errors but i can't. i am using the structured meshing using ICEM. turbulence modeling i am using are SA & K-OMEGA(SST). when i trying to refine the mesh to reduce error and close to experimental datas @ 3e+6 reynolds number error results are more than above( 7.5 and 12%) i dont know how to overcome this problem please help me.... thank you 
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