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TURBULENCE MODEL NUMERICAL ANALYSIS

3D ONERA M6 Wing Validation Case

The purpose here is to provide a test case for a turbulent flow over a transonic wing. Over the years, the ONERA M6 experiment (Schmitt, V. and Charpin, F., "Pressure Distributions on the ONERA-M6-Wing at Transonic Mach Numbers," Experimental Data Base for Computer Program Assessment. Report of the Fluid Dynamics Panel Working Group 04, AGARD AR-138, May 1979, https://www.sto.nato.int/publications/AGARD/AGARD-AR-138/AGARD-AR-138.pdf) has been a widely used case for CFD "validation." This wing is used here primarily for numerical analysis of turbulence model simulations; e.g., convergence properties, effect of order of accuracy, etc.

Recently, a group at ONERA has looked into the M6 model and its past experiments in greater detail. See AIAA Papers 2015-1745, https://doi.org/10.2514/6.2015-1745 and 2016-1357, https://doi.org/10.2514/6.2016-1357. As part of this effort, the group has created a CAD geometry for the wing, provided below. In this geometry, the trailing edge of the wing has been made sharp for the purposes of this particular CFD exercise, as described in AIAA Paper 2016-1357. (The original ONERA M6 wing has a moderately thick trailing edge; see AileM6_with_thick_TE.igs.) Additional details are provided in: ONERA_M6_Test_Case_TMR.pdf.

For reference, the ONERA section coordinates (with blunt T.E.) are provided below. The first file corresponds to the ONERA-D wing section that lies normal to a generator build at 40.18% chord (the generator build line is shown as a dash-dot line in Figure 1 of ONERA_M6_Test_Case_TMR.pdf). The second file (taken from https://www.grc.nasa.gov/WWW/wind/valid/m6wing/m6wing.html), corresponds to the streamwise coordinates taken along the root (y=0). Both files are scaled to have 0 < x < 1.

• profile_ONERA-D.dat
• profile_M6_streamwise_alongy=0.dat

CAD Geometry (with sharp T.E.):

• IGS file
• STP file
• Parasolid (x_t) file

Some of the wing geometry data extracted from the CAD:

• Root chord: 810.491484086 mm
• Semispan (last section): 1196.300000084 mm
• Tip chord (last section): 455.914415721 mm
• Leading Edge Sweep: 29.9990 degrees
• Trailing Edge Sweep: 15.6918 degrees
• Rounded Tip Semispan: 1218.535 mm

Test cases description:

• Case 2308: M_inf=0.84, Re_{c_root}=14.6 x 10⁶, AoA=3.06 deg, T_inf=540 R.
• Case 2565: M_inf=0.84, Re_{c_root}=14.6 x 10⁶, AoA=6.06 deg, T_inf=540 R.
• For the purposes of the CFD V&V exercise performed here (for comparisons between codes), only the wing with the SHARP trailing edge should be used. The Reynolds number of the original experiment (based on the blunt mean aerodynamic chord of 646.07 mm of the model), was Re_MAC=11.72 x 10⁶ for Case 2308 and Re_MAC=11.71 x 10⁶ for Case 2565. However, for the purposes of this CFD exercise, Re_{c_root}=14.6 x 10⁶ (based on root chord with sharp trailing edge) should be used for both cases. This value approximately corresponds with the original experiment.
• Note that Cp data are available for 7 span stations: eta = y/b = 0.2, 0.44, 0.65, 0.8, 0.9, 0.96, and 0.99. The original reference (and some other websites) list the 6th station to be at eta = y/b = 0.95, but recent measurements on the ONERA model have confirmed that it should be 0.96 instead.

Grid generation programs are available in the following link. Note that the programs create grids that are normalized so that the root chord = 1. With the new scaling, the following geometry information for computing forces and moment should be used:

• Reference area = 1.15315084119231
• Reference mean aerodynamic chord = 0.801672958512342
• Reference semispan = 1.47601797621980
• The x,y,z moment centers are all taken to be 0.0

GRIDS

Experimental Cp data:

• Case_2308.dat
• Case_2565.dat

What to Expect:

RESULTS	LINK TO EQUATIONS	MRR Level
SA-neg	SA-neg eqns	4

(Other turbulence model results may be added in the future.)
 
 

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Last Updated: 11/10/2021