[ht2017]

Hi everyone,
I am using KomegaSSTLM for my simulation. But I don't know the reason why my result incorrect?
this is my case:
I run the simulation for A-airfoil with inlet condition is M = 0.15,Re = 2.1e6, alpha =13.1,Tu = 0.1%,μ_t/μ =2.
I calculate the coefficients:
K =3/2(UI)^2 = 3/2 (51.9*0.1%)^2=0.00404; ω = ρ* k/μ*(μ_t/μ)^-1
ω = 1.225*0.00404/(1.846*10^-5)*(2)^-1=134.05;
gamma I choose 1. gama = 1;
Re_thetat = (1173.51-589.428*Tu+0.2196/(Tu^2))*F(λθ) Tu<= 1.3;
Re_thetat = 331.50*(Tu-0.5658)^-0.671*F(λθ) Tu >1.3;
F(λθ) =1-1(-12.986*λθ-123.66*λθ^2-405.689*λθ^3)*e^(Tu/1.5)^1.5 λθ<=0;
F(λθ) =1+0.275*(1-e^(-35.*λθ))*e^(Tu/0.5) λθ>0;

From this function: I choose λθ = 0 ( I not sure it is correct I only think Du/Ds = 0 Inferred λθ = 0) then I calculate Re_thetat = 1.365e+3.

I have the coefficients:
K =0.00404;ω =134.05,gamma = 1,Re_theta = 1.365e+3 this is the coefficient value for inlet condition.

And Then I set up following the tutorial incompressible/simpleFoam/T3A. I change the geometry to A-airfoil and set up the value coefficient and I run it.
The finally, I run with comment line "simpleFoam -postProcess -func 'wallShearStress' and paraFoam. In the paraview I load out the data in the surface top-Airfoil. I plot the wallshearstress following the x-axis. But my result incorrect.

If anyone has experienced run with KomegaSSTLM for airfoil Please teache me. I really hope anyone who can help me resolve it.
Thank you very much