single point optimization failed to do the optimization seeking for help in this issues

[MachAeroDeveloper]

airfoilopt code.txt
Dear MachAero Support Team,

I hope this message finds you well. I am currently working on an optimization project using MachAero for an airfoil with a specific shape. The optimization process runs successfully, but I am facing a challenge in obtaining the profile of the optimized airfoil.

To provide you with more details, I have modified the design variables to include only the shape FFD control variables. I will share with you the relevant sections of the code that I have used, along with the optimization results.

mycd = 0.01
# angle of attack
alpha = 1.5
# mach number
mach = 0.15
# cruising altitude
alt = 13
.
.

DVGeo.addLocalDV("shape", lower=-1.0, upper=1.0, axis="y", scale=1.0)


le = 0.001
leList = [[le, 0, le], [le, 0, 1.0 - le]]
teList = [[1.0 - le, 0, le], [1.0 - le, 0, 1.0 - le]]
.
.
DVCon.addVolumeConstraint(leList, teList, 2, 100, lower=1, scaled=True)
DVCon.addThicknessConstraints2D(leList, teList, 2, 100, lower=0.1, upper=3.0)
.
.
.
funcs["obj"] = 1/funcs[ap["cl"]]
    funcs["cd_con_" + ap.name] = funcs[ap["cd"]] - mycd
.
.
# Add objective
optProb.addObj("obj", scale=1.0)

# Add variables from the AeroProblem
ap.addVariablesPyOpt(optProb)

# Add DVGeo variables
DVGeo.addVariablesPyOpt(optProb)

# Add constraints
DVCon.addConstraintsPyOpt(optProb)
optProb.addCon("cd_con_" + ap.name, lower=0.0, upper=0.0, scale=1.0)

Here is a brief overview of the issue:

Optimization Success: The optimization terminates successfully, indicating that the process is working fine.

Profile Retrieval Issue: Despite the successful optimization, I am unable to retrieve the profile of the airfoil.

Design Variable Modification: I have narrowed down the design variables to include only the shape FFD control variables.

Objective Function Change: I have adjusted the objective function to be 1/cl to achieve maximization of the airfoil.

I kindly request your assistance in resolving this issue. If you could review the provided code snippets and share any insights or recommendations on how to obtain the airfoil profile post-optimization, it would be immensely helpful.

I understand that you may need additional details, and I am more than willing to provide any further information required. Your support in addressing this matter is greatly appreciated.

Thank you for your time and assistance.

Best regards,
ailun
Master researcher



out.txt