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Transonic turbulent flow past ONERA M6 wing

In this study, computations are performed for steady, transonic and turbulent flow past ONERA-M6 configuration. This test case is one of the first validation cases considered using HiFUN.

Grid Details

Zoomed view of grid
Grid
S.No
Grid Type
Elements
No of cells (Mn)
1
Unstructured
Prisms and tetrahedrons
24,37,644

Test Conditions

Altitude
Angle of Attack (°)
Mach Number (°)
Reynolds Number (Mn/Mtr)
-
3.06°
0.84
11.72 millions

Results

The Lambda-shock on the upper surface of the wing is well captured in the computations using HiFUN.
Pressure contours
Pressure fill plot
Pressure contours
Pressure distribution at various span-wise stations on the wing surface compares well with the experimental results.
20% of span
44% of span
65% of span
80% of span
90% of span
95% of span
99% of span

References

Schmitt V. and F. Charpin,"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.

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