problem numerical results of lift and drag in airfoil simulation using fluent solver -- CFD Online Discussion Forums

June 7, 2018, 02:59	problem numerical results of lift and drag in airfoil simulation using fluent solver	#1
Mohammad1994 New Member Mohammmad ali gheidi shahran Join Date: Jul 2017 Location: Tehran Posts: 6 Rep Power: 9	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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