[akulagr]

Hello all

I've been trying to setup a case involving flow over a wall mounted hump (part of nasa case 3 in advance turbulence modelling. see link below). I've found that the case is pretty sensible to the boundary conditions, so far i tried many different combinations, where perhaps the best results were given by using the following conditions:
density based solver
Ideal-gas for air
Sutherland for viscosity (default settings)


Inlet set as pressure-farfield:
-gauge pressure set as 101325Pa
-Mach set to 0.1
-temperature set to 298.33 K
outlet set as pressure-outlet
-gauge pressure set as 101301Pa
temperature set to 298.33K

operating conditions set at 0Pa

im struggling to match my results with the experimental data available for the case, specially the skin friction coefficient (Cf) and velocity profiles at different locations.
with these boundary conditions i get an oscillating behaviour in the scaled residuals (when running second order) making it hard to reach convergence. such behaviour has lead me to belive that the boundary conditions have been set incorrectly.
please if anyone has any suggestions on the correct settings for this problem it would be greatly appreciated.

this link provides an overview of the case: http://turbmodels.larc.nasa.gov/nasahump_val.html

im essentially trying to model condition 1 which has no flow through the synthetic jet.
Regards
david