[zkdkeen]

Hello everyone!
I am simulating flow around fanwing as I posted several days before. After doing and adusting as Mr.Gorrocks suggested, the case successfully run and yeilds some results with fine velocity filed stucture as some article, but the Lift is much less than the same case motioned in the article. Say, with 6.812m/s in flow velocity, 1480 rpm fan rotation angle velocity, zero AoA and same geomety, the aritcle presents CL is about 8 (Q depending on in flow vel and S depending on whole wing aera), but my calculationg results CL as about 2.

The case in pre cfx I configured is general type, inner domain rotating, outter stationary, transient simulating, TRS interface, and sst turb model. And the grid is unstructured with 70,000 and 210,000 elements as coarsen and refined mesh.

So, my question is why the CL is so small? How to config my parameters in pre cfx to improve it? Any suggestion from any body will be highly appreciated!

Regards
keen

[ghorrocks]

http://www.cfd-online.com/Wiki/Ansys..._inaccurate.3F

[zkdkeen]

Originally Posted by ghorrocks

http://www.cfd-online.com/Wiki/Ansys..._inaccurate.3F

Oh, I see. I will follow the steps from the FAQ suggestion.
By the way, as to my case, the interface is a whole 360 degree circle between the wing and blades, so should I set the "pitch change" option to "None" or "Automatic"?

[ghorrocks]

It does not matter. Both will not apply a pitch change.

[zkdkeen]

Got it! Thanks a lot! Mr. Ghorrocks