maximization lift coefficient for an the objective function for multiple point airfoil optimization

[EngJamal2023]

I'm hoping that the community can help me find an error in my code. I created this code to calculate optimization, and I made some modifications to it. However, I'm encountering an error and would appreciate any assistance in identifying and fixing the issue. I've included the relevant code snippet below for reference.
i use prefoil model to create the distribution the point around airfoil

mach = [0.15, 0.044]
alt = [100, 80]
alpha = [1.5, 10.17]
mycd = [0.01, 0.024]

and i put some of adflow solver option for low mach number as following

    "liftIndex": 2,
    "infchangecorrection": True,
    "writeTecplotSurfaceSolution": False,
    "acousticScaleFactor":0.01,
    "ANKCharTimeStepType": "VLR",

because i use analysi for airfoil for wind turbine i change the thickness

DVCon.addThicknessConstraints2D(leList, teList, 2, 100, lower=0.1, upper=1.15,scaled=True)
i change here the opjective function and drag constraint as following

        funcs["obj"] -= funcs[ap["cl"]] / nFlowCases
        funcs["cd_con_" + ap.name] = funcs[ap["cd"]] - mycd[i]

also i change the scale of the objective function

optProb.addObj("obj", scale=1.0)

i hope if there is mistake fill me with correction it is so glad for your help

[MachAeroDeveloper]

please anyone answer me please ###