[mervisgurban]

Hello everyone,

I am running a turbomachinery analysis on CFL3d. Model is Rotor67, mesh is from the CGNS lab with no tip gap.

I am using non-inertial frame for which the rotational velocity is calculated as below:

omegax=realomega(degree/sec)xreferencelength/speedofsound

The rotational speed is 16043 rpm, and the model is in mm but cfl3d is using feet, so referencelength is chosen as 0.003 feet (mm to feet scale). and speed of sound is calculated by the input temperature.

Inlet boundary condition is total pressure and temperature ratio. Outlet boundary condition is static pressure. Trying to adjust them for mass flow rate and am trying to remain close to the experimental results.

However, I can't seem to get it work. Mass flow rate is not equal at inlet and exit. Residual is oscillatory, I am running more and more iterations, but it doesn't seem to get any better. Now I am trying lowering the dt, but I am not sure if it will work.

What am I doing wrong? What should I do?