failed optimization at low mach number 0.044 at maximization lift for single point optimization for same tutorial NACA0012

[EngJamal2023]

I kindly request assistance in achieving a favorable outcome for my single point optimization case. Despite dedicating an entire month to identifying my mistakes, I have been unable to pinpoint the error I made. I am hopeful that you can provide me with guidance. To this end, I have made modifications to the opt_airfoil.py code as outlined below:

and i have been changed on the objective function and the sensitivity function as following ;

and also the drag constraint as following 👍

I sincerely hope to receive assistance and guidance regarding my current issues. It would be greatly appreciated if you could suggest a guide book or provide tutorials on Python scripting for single point optimization and other optimization techniques. Despite my extensive reading, I have been unable to find the answers to my questions. Therefore, I kindly request your help in identifying the possible changes that I should focus on when conducting an analysis on different airfoils to address the issue of solution divergence. Your support in this matter would be invaluable to me.