Trouble when using MUSCL scheme on ONERA M6 wing
 

Hi!

I am currently running a simulation on the ONERA M6 wing. The Reynolds number is 11.71 million, the Mach number 0.8372 and the angle of attack is 6.06°. The simulation is running in 3ddp with a structured mesh of 300,000 cells.

I am using k-epsilon standard as viscous model and an implicit density-based solver. I have first made the solution converged in 2nd order upwind but when I have switched to 3rd order MUSCL, I have the "turbulent viscosity limited to viscosity ratio" problem which has appeared after only 5 iterations. The number of cells concerned about this problem increased until 14,000.

I have read in Fluent user's guide that there is no flux limiters in the MUSCL scheme inplemented.
So my question is: do you think my problem is due to this specification?

Thanks.
Regards,
Aurélien

Mr Malik
 

Hi Aurélien,

I am doing a project on shape optimisation of ONERA M6 wing. Can you please send me the CAD geometry of this wing that I can upload in ICEM. If possible can you also send me some simulations of M^ wing


Regards,
Malik

Malik
 

Hi Aurélien,

I am in severe need of ONERA M6 wing 3D mesh. i need both coarse and fine mesh that i can open in ICEM and then run simulations in Fluent. Can you plz send it to me on s.malik.eng@gmail.com