Hello,
I'm new to CFD. I'm currently simulating flow over 3D wing (NACA 0018) with no taper. I have used symmetric boundary condition for my flow domain. I'm getting half the value Cl when compared to the experimental results. Does the symmetric boundary condition affect my Cl values or is there something else that could cause this.
Please specify more precisely, where you specify symmetry BC. I previously used zero gradients or symmetry at sides. But more wise would be using Inlet/outlet/ with pressure (I used OpenFOAM) especially for transsonic regimes. Your CL could suffer from small doain, or poor mesh as well.
Thank u for
replying.
dear Vadim, i have mentioned the symmetry boundary condition on the top, bottom and sides of the flow domain. But now when i have given pressure far field for all the boundaries and simulated, I'm getting proper answers.
Dear abdul ,
by aerodynamic coefficient i mean the Cl in the lift equation.
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