[tum-student]

Hello,
I am simulating a diamond airfoil at supersonic flow at Mach 3. I am using rhoCentralFoam as a solver and k-w SST turbulence model to solve this case. When I use velocity boundary condition as "slip" for the airfoil boundary, my run is successful without any problems, but when I change the BC to "noSlip". I am getting a "Negative Initial Temperature T0" error and the run crashes.
I have also tried to limit the temperature using fvOptions, but it's not working. I have also checked by refining the mesh, but still, the problem exists.

Please help me.

Other boundary conditions for airfoil are as follows:
p - type zeroGradient
T - type zeroGradient
alphat - type compressible::alphatWallFunction, value uniform 8.88e-9
epsilon - type epsilonWallFunction, value uniform 365627.58
k - type kqRWallFunction, value uniform 901.31
nut - type nutkWallFunction, value uniform 0.199
omega - type omegaWallFunction, value uniform 4507.4