[Crank-Shaft]

Hello Forum regulars and guests,

I have recently started working with a 2D geometry consisting of a bump on a wall, a defined inlet and outlet and symmetry conditions on the rest of the exterior boundaries. This is described in detailed within the images attached. This is a benchmark study from NASA and I would like to use it as a reference for code verification. (For Details - http://turbmodels.larc.nasa.gov/bump.html)

I am looking for suggestions to implement the boundary conditions required, to match the reference results. I am trying to obtain steady state solutions using an ideal-gas model, with gravitational acceleration in -y axis. The current boundary conditions including the pressure outlet and inlet have an operating pressure of 101 325 Pa with a gauge pressure set to (101 325 x 0.02828) Pa. This pressure gradient results in a velocity of 69.7 m/s which satisfies the M=0.2 condition. I currently have the energy equation turned off, since I am working through the preliminary stages of the simulation setup. I have received several warnings and recommendations when I clicked Check Setup before commencing with the solver iterations, as shown in the image.

All the convergence criteria for the residuals were defined as 1e-6 however, the continuity simply remains at 1e-2 despite the large number of iterations performed. I tried changing the momentum relaxation factor from 0.8 to 0.5 however, this only had a minimal effect.

Please help me implement the boundary conditions outlined in the first two images and also provide some guidance to improve the absolute continuity residuals. I look forward to your comments.