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June 8, 2022, 14:44
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Simulation NACA 0018, Cl, Cm, Cd
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New Member
Vyacheslav Papkov
Join Date: May 2022
Posts: 5
Rep Power: 3  |
Hello! I am modeling the aerodynamic profile of a NACA 0018 wing in a 2d formulation of the problem. I have an error when getting Sd and Sf in +- 0.15. For example, if I have a theoretical value of +-0.6 at an angle of attack of 16 degrees, then my result is 0.45. How can this be fixed? SST turbulence model, screenshots attached below
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| airfoil 2d, airfoil mesh, help me, mesh 2d, naca 0018 |
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Linear Mode
