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2D NACA 0012 Airfoil Validation Case

SSG/LRR-RSM-w2012 Model Results
 

Link to SSG/LRR-RSM-w2012 equations

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 the NACA 0012 Numerical Analysis Case for a representative verification exercise of this airfoil case.)

Above SSG/LRR-RSM-w2012 results are from CFL3D, FUN3D, and TAU on the 897x257 grid. Both CFL3D and FUN3D used freestream turbulence intensity=0.052% and freestream turbulent viscosity (relative to laminar)=0.009 (additional details can be found in the CFL3D User's Manual, Appendix H), while TAU used freestream turbulence intensity=0.1% and freestream turbulent viscosity (relative to laminar)=0.1. Please read note 5 on Notes on running CFD page. Results are overall very close between the three codes, with the largest difference seen in drag at alpha=15 deg (2.5% difference). These discrepancies between codes are due to discretization errors, boundary condition differences, and/or possible code-to-code implementation-detail differences. See NACA 0012 Numerical Analysis Page for more discussion about numerical issues associated with the NACA 0012 airfoil case. Note that these are compressible code results at "essentially incompressible" conditions of M=0.15. There may be a very small influence of compressibility. Only the CFD data files from CFL3D's SSG/LRR-RSM-w2012 results are given here for reference: n0012clcd_cfl3d_ssglrrrsm.dat, n0012cp_cfl3d_ssglrrrsm.dat, and n0012cf_cfl3d_ssglrrrsm.dat. A typical CFL3D input file is: n0012_cfl3d_typical_ssglrrrsm.inp. A typical FUN3D input file is: fun3d.nml_typical_ssglrr_2.

Behavior of model near CLmax:

The behavior of the SSG/LRR-RSM-w2012 model near maximum lift for this 2-D case is shown in the following plots (CFL3D only). The cases were run every 1 deg (starting at 15 deg.), at least until C_L,max was approximately attained. An approximate C_L,max range from experiments (McCroskey, AGARD CP-429, July 1988; also NASA TM 100019, October 1987) is highlighted in the first plot by green dashed lines. Note, however, that experimental data near maximum lift no doubt contains a significant degree of three-dimensionality. Also, these CFD results are still on the 897x257 grid, and there is likely to be significantly more grid sensitivity for the higher angles of attack than for the lower angles of attack shown above. Therefore, the results below should only be viewed qualitatively.

 
 

Jump to: SA Results,  SA-RC Results,  SSTm Results,  SST-Vm Results,  Wilcox2006-klim-m Results,  K-kL-MEAH2015m Results,  EASMko2003-S Results,  K-e-Rt Results

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Last Updated: 03/04/2025