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2D NACA 0012 Airfoil Validation

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Old   May 30, 2013, 10:22
Default 2D NACA 0012 Airfoil Validation
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Hi everyone,

I am doing simulation for NACA 0012 foil and I want to compare with the experimental data as well as numerical data from NASA.
http://turbmodels.larc.nasa.gov/naca0012_val_sst.html

However, I still confuse about the turbulent condition as follow:
# NACA 0012, 897x257 grid, CFL3D with SST model,
# freestream k/a_inf^2=9.e-9
# freestream omega*mu_inf/(rho_inf*a_inf^2)=1.e-6
# Lifting results have point vortex farfield correction on
# Note: results very near T.E. have high numerical error - see Swanson & Turkel, AIAA 87-1107, 1987
# (Results here given to greater accuracy than convergence tolerance)

What do the # freestream k/a_inf^2=9.e-9
and # freestream omega*mu_inf/(rho_inf*a_inf^2)=1.e-6
mean?
I guess that these are the input parameters for turbulent model. But I do not know how to implement these into CFD codes.
Please explain for me!
Thank you very much!
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