Transonic ONERA M6 Wing

Introduction

The ONERA M6 wing is a wing geometry designed in 1972 by ONERA, the French national aerospace laboratory, for the study of three-dimensional supersonic flows. The wing geometry is simple, but has long been used as a problem for CFD validation because it allows observation of various phenomena in supersonic flows, such as turbulent boundary layer transitions, shock wave-boundary layer interactions, and flow separation.

Conditions

Compressible steady flow
Mach No. = 0.8395
Static Pressure = 80558.7 Pa
Static Temperature = 255.36 K
Reynolds No. = 11.72E06
Angle of Attack = 3.06 deg
Reference length = 0.64607 m
Reference area = 1.51499432 m^2

FAMUS Setup

Number of points of octree is about 2.5 milion
Number of points of boundary layer is about 3.6 milion
Viscosity model : SST k-omega turbulence model
Discretization = MLP MINMOD
Time marching = LU-SGS
Flux scheme = M-AUSMPW+

Simulation Result

Pressure contour(AOA=11)

Pressure coefficient(The number on top means the wing span position)

References

Schmitt, V. and Charpin, F. Pressure distributions on the onera-m6-wing at transonic mach numbers. AGARD-AR-138, 1979.