failure mesh output when i do single point optimization for airfoil shape optimization for

[MachAeroDeveloper]

Dear all,

I hope someone can help me understand the issue I'm facing. I need to perform single-point optimization for the DU91-W2-250 airfoil, aiming to maximize the lift coefficient while maintaining a drag constraint. I've modified the code from the NACA0012 airfoil tutorial and adjusted the parameters for my specific problem. However, the mesh, as shown in the attached figure, has failed. Additionally, the results of my objective function are far from the desired solution, and I am not seeing any increase in lift, nor am I approaching the maximization of the lift coefficient.

I've tried different objective functions, such as:

-C_l
C_d/C_l
1/C_l
0.01C_d - 0.5C_l

None of these have worked well. Interestingly, when I minimized drag subject to a lift constraint, the optimization worked fine, but maximizing the lift has not been successful.

Please, I urgently need assistance with this problem. Any help or guidance would be greatly appreciated.

Thank you.