[dengdeng]

Hi there,

I am simulating a supersonic flow case with a flat plate of zero angle of attack using Large Eddy Simulation (LES). I would like to reproduce the solution from a paper, in which the boundary layer of the flat plate follows a laminar-transition-turbulent pattern.
Since this is a supersonic case, I would like to use density-based solver and WALE is chosen as the subgrid-scale model. As is described in the Help that perturbations could be assigned to the inlet for the LES model, I do successfully find the option of "Fluctuating Velocity Algorithm" for Velocity Inlet type boundary while using pressure-based solver. However, this option disappears when I switch the solver to the density-based one.
Do you have any solution to this problem? Or does anyone has other methods to assign the turbulence intensity at the supersonic inlet while running LES?

Regards.