[Brathmann]

Hello everybody.

For a propeller-like geometry in a closed volume I want to model the air flow, namely dynamic pressure, resulting from the rotor movement. Most hints how to do that which I found pointed out to use a rotating reference frame. I did that but end up with results that don't match each other at the contact faces between the moving and the rotating fluid zone. Do you have any idea what the problem might bee?

Here is what I did so far: (If you lack information, I's be happy to provide more. I'm still not so sure, which information is relevant for the problem)
I modeled a cyclic periodic region of the problem, meshed it with Face Sizings and obtained a mesh of about 0.2 othogonal quality and 10 aspect ration. Which isn't super, as far as I got it, but did lead to convergence. After defining the small, disk like fluid zone (s. pic: PeriodicRegion) as rotationally moving frame with rot. velocity of 90 rad and the adjacent rotor-wall as rotationally moving wall with relative velocity of 0m/s i sucessfully made periodic boundaries for the symmetry boundaries in the model and set the contact region between the moving fluidzone and the rest of the flow channel as standard interfaces.
With the standard visous k-e-model, Coupled Scheme as Solution Methods using Second Order Upwind discretizations for Momentum, Turbulent Kinetic Energy and Turbulent Dissipation Rate convergence is quick (worst convergence is Continuity with 0.001) and results seem reasonable.

The problem is, that the calculated values clearly don't match in the contact area of the two fluid zones as you can see in pic. PressureDyn. The spare area in the plane is the airfoil, rotating away from the spectator around the y-axis situated at the origin to the left of the countour plane.

Any hints? I would appreciate a lot.
Have a nice day
Brathmann

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