Issue with Lift and Drag Coefficient Calculation Due to Mesh Resolution in mesh

[MachAeroDeveloper]

Description of feature

i am trying to calculate the lift and drag coeffieciet for airfoil but i face this problem

this problem it becuse the mesh when i increased the n from 159 to 399 this problem it cancelled and i am sure becuse the mesh so i will attach the result of my mesh to see where is my problem and i hope i can get help from one of developer and i am so glad if some one help me in this issues .
this the file of the log out and please check it what the problem
"N": 159,
"s0": 1.2e-5,
"marchDist": 100.0,
"nodeTol": 1e-10,
"panelEps": 1e-10,
cMax": 1.08,
"slExp": 0.05,
meshlog.txt
what i need what the tools and comand in cgns-utils that i can use it to solve this problem and i try to use refine and some of the other tools but i can not get any improvment please solve this