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Return to: 2D Airfoil Near-Wake Case Intro Page
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2D Airfoil Near-Wake Validation Case
SSTm Model Results
Link to SSTm equations
Previously on this page the results were reported as SST solutions, but more properly they should be referred
to as SSTm. Essentially no difference is expected.
Note that thorough
grid studies were not performed for validation cases such as this one.
Some effort was made to ensure reasonable grid resolutions, but there may still be
small noticeable discretization errors. Therefore, these validation results shown should be considered
representative, but not "truth."
(See VERIF/2DANW for a verification version of this airfoil case.)
IMPORTANT NOTE: This validation case uses grids that only extend 20c from the airfoil.
It was later discovered that this farfield grid extent is too small for verification purposes.
Therefore, any results using only 20c grid extent should be viewed WITH CAUTION.
The verification case using 500c grid extent can be found at the link above.
The plots shown compare the SSTm results from two independent
CFD codes: CFL3D and FUN3D, along with experimental data.
Both CFL3D and FUN3D used freestream turbulence intensity=0.088% and freestream turbulent viscosity (relative to laminar)=0.009
(additional details can be found in the CFL3D User's Manual, Appendix H).
Please read note 5 on Notes on running CFD page.
These results are from the second-finest grid (1121x193).
Both codes gave nearly identical results to each other.
(On this grid level, CL=0.1574 and CD=0.01011 for CFL3D, and CL=0.1556 and CD=0.01015 for FUN3D.)
Note that these are compressible code results at "essentially incompressible" conditions of M=0.088.
There may be a very small influence of compressibility.
The data files from CFL3D are given here:
nak_cfl3d_vel_sst.dat,
nak_cfl3d_uv_sst.dat,
(Note: the profiles have been interpolated using Tecplot software onto pre-set points, that may or may
not correspond to the actual grid points or grid cells used in the computation.)
A typical CFL3D input file is:
nak_cfl3d_typical_sst.inp.
A typical FUN3D input file is:
fun3d.nml_typical_sst_2.
Jump to: SA Results,
SSG/LRR-RSM-w2012 Results,
Wilcox2006-klim-m Results,
K-kL-MEAH2015m Results,
EASMko2003-S Results,
K-e-Rt Results Return to: 2D Airfoil Near-Wake Case Intro Page Return to: Turbulence Modeling Resource Home Page
Responsible NASA Official:
Ethan Vogel
Page Curator:
Clark Pederson
Last Updated: 03/03/2025