NACA 4412 2D Fluent Analysis

dbh0006 · March 31, 2019, 15:49

Hello!

I'm using the ANSYS Student software and did an analysis in fluent of a NACA 4412 airfoil (2D) at a Reynolds number of roughly 100,000. However, the lift and drag coefficients are not the same as the theoretical values (from airfoiltools.com), and they are actually quite different. The difference between the theoretical and the Fluent results also increases as the angle of attack gets further away from 0. I don't know why this is? I played around with the setup a lot, and the mesh looks pretty good to me and the quality of the mesh is also high. Can someone give me a few pointers so that I can get better results?

Thanks!

ngoctm · June 3, 2019, 05:47

Hi,

Please notice the Reference Values.

The Reference Values task page allows you to set the reference quantities used for computing normalized flow field variables

Best,

March 31, 2019, 15:49	NACA 4412 2D Fluent Analysis	#1
dbh0006 New Member Daniel H Join Date: Mar 2019 Posts: 5 Rep Power: 7	Hello! I'm using the ANSYS Student software and did an analysis in fluent of a NACA 4412 airfoil (2D) at a Reynolds number of roughly 100,000. However, the lift and drag coefficients are not the same as the theoretical values (from airfoiltools.com), and they are actually quite different. The difference between the theoretical and the Fluent results also increases as the angle of attack gets further away from 0. I don't know why this is? I played around with the setup a lot, and the mesh looks pretty good to me and the quality of the mesh is also high. Can someone give me a few pointers so that I can get better results? Thanks!

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June 3, 2019, 05:47		#2
ngoctm Member Join Date: Mar 2009 Location: Vietnam Posts: 36 Rep Power: 18	Hi, Please notice the Reference Values. The Reference Values task page allows you to set the reference quantities used for computing normalized flow field variables Best,