I am using the fluent solver to trying and resolve a simplified case of a deployed parachute at Mach 1.85. Main issue is that the bow shock and wakes are not resolving properly, picture attached. I am using a pressure inlet where the gauge pressure is the dynamic pressure of the system and the operating pressure is the air pressure at my desired altitude. I could use some help on this setup. Also wondering where there is some good literature about the implications of playing with the turbulent viscosity ratios/numbers beyond the users manual.
Would it also be good to set my fluid density to ideal gas, and the solver to density based? This is my current set-up. Also using SA turbulence model and energy equation is on.
Mesh is about 9Mil elements, probably could be resolved better around geometry edges but when I use sphere of influence it blows up the element number, any suggestions there? Also thinking of making a model of just the capsule and trying to create the bow shock there at a far lower element count. So suggestions for how to fully properly resolve a 3D mesh for supersonic flow would be great.
Again my main issue right now is that the pressure profile is not correct at all, also getting these messages in the fluent console each iteration and my residuals blow up to e+12. Also confused why the first message references a time step but I am just solving 1000 iterations frozen in time. Assuming it is something about the solver giving the problem some sort of time domain/parameter so that it can resolve the simulation?
time step reduced in 131 cells due to excessive temperature change
absolute pressure limited to 1.000000e+00 in 84 cells on zone 4
absolute pressure limited to 5.000000e+10 in 364 cells on zone 4
temperature limited to 1.000000e+00 in 85 cells on zone 4
temperature limited to 5.000000e+03 in 2358 cells on zone 4
Thanks for reading,