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January 15, 2022, 11:01
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NACA 0012 Drag Minimization
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New Member
Abhijith
Join Date: Nov 2020
Location: United Kingdom
Posts: 19
Rep Power: 6  |
I'm trying to minimize the drag of the NACA 0012 airfoil. Please find the details in the attached image. It is a symmetric case with only the upper surface.
I'm trying the following constraints: OPT_OBJECTIVE= DRAG OPT_CONSTRAINT= ( AIRFOIL_THICKNESS > 0.6 ) * 1.0 But the results are wrong. I think the problem is with my constraints. Please help me fix this. |
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