Trouble with airfoil drag prediction.

Zmur · March 25, 2009, 02:11

Hello.
I know quite a few questions of this sort have been posted here, so I looked through some pages but found nothing useful for my case.

I try to calculate Cl and Cd for an airfoil at Re=2e6. I get more or less accurate results for Cl but Cd is nit correct no matter what I'm doing to the mesh. I tried over 20 different mesh sizes, Inflation settings and so on but it doesn't seem to work...
Could you please suggest some "example" settings or something like that for CFX-mesh and CFX-Pre so I have a starting point?

ghorrocks · March 25, 2009, 16:48

Hi,

Can you describe what you are trying to model? Is the wing stalled? Does it have small separations or fully attached flow? Is turbulence transition important? 2D or 3D? Compressible or incompressible? What Mach number?

Glenn Horrocks

Zmur · March 26, 2009, 02:06

Sorry

It is a NACA 23020 airfoil with 1.2m long chord. It is at 0degree angle of attack. The simulation is 2D, the velocity of flow is 20m\s, normal pressure, density = 1.184.
Using k-omega turbulence model, Eddy Length Scale in Global Initialisastion is set to 0.1m. Y-plus is somewhere around 1 in dense meshes but not more than 12.
I need only accurate Cd and Cl that are close to the experimental data. Right now I'm getting Cl = 0.04-0.06 and Cd = 0.01, but it should be: Cl = 0.06 and Cd = 0.006.

Yesterday I somehow achieved almost correct results but then I decreased the mesh scale (0.5 which led to 700 000+ element mesh) and the results were incorrect (similar to above).

ahlo7 · March 30, 2009, 10:34

Quote:

Originally Posted by Zmur

Sorry

It is a NACA 23020 airfoil with 1.2m long chord. It is at 0degree angle of attack. The simulation is 2D, the velocity of flow is 20m\s, normal pressure, density = 1.184.
Using k-omega turbulence model, Eddy Length Scale in Global Initialisastion is set to 0.1m. Y-plus is somewhere around 1 in dense meshes but not more than 12.
I need only accurate Cd and Cl that are close to the experimental data. Right now I'm getting Cl = 0.04-0.06 and Cd = 0.01, but it should be: Cl = 0.06 and Cd = 0.006.

Yesterday I somehow achieved almost correct results but then I decreased the mesh scale (0.5 which led to 700 000+ element mesh) and the results were incorrect (similar to above).

Try SST turbulece model

Zmur · March 30, 2009, 13:47

Quote:

Originally Posted by ahlo7

Try SST turbulece model

I did... Same results.

March 25, 2009, 02:11	Trouble with airfoil drag prediction.	#1
Zmur New Member Yury Timofeyev Join Date: Mar 2009 Location: Latvia Posts: 16 Rep Power: 17	Hello. I know quite a few questions of this sort have been posted here, so I looked through some pages but found nothing useful for my case. I try to calculate Cl and Cd for an airfoil at Re=2e6. I get more or less accurate results for Cl but Cd is nit correct no matter what I'm doing to the mesh. I tried over 20 different mesh sizes, Inflation settings and so on but it doesn't seem to work... Could you please suggest some "example" settings or something like that for CFX-mesh and CFX-Pre so I have a starting point?

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March 25, 2009, 16:48		#2
ghorrocks Super Moderator Glenn Horrocks Join Date: Mar 2009 Location: Sydney, Australia Posts: 17,700 Rep Power: 143	Hi, Can you describe what you are trying to model? Is the wing stalled? Does it have small separations or fully attached flow? Is turbulence transition important? 2D or 3D? Compressible or incompressible? What Mach number? Glenn Horrocks

March 26, 2009, 02:06		#3
Zmur New Member Yury Timofeyev Join Date: Mar 2009 Location: Latvia Posts: 16 Rep Power: 17	Sorry It is a NACA 23020 airfoil with 1.2m long chord. It is at 0degree angle of attack. The simulation is 2D, the velocity of flow is 20m\s, normal pressure, density = 1.184. Using k-omega turbulence model, Eddy Length Scale in Global Initialisastion is set to 0.1m. Y-plus is somewhere around 1 in dense meshes but not more than 12. I need only accurate Cd and Cl that are close to the experimental data. Right now I'm getting Cl = 0.04-0.06 and Cd = 0.01, but it should be: Cl = 0.06 and Cd = 0.006. Yesterday I somehow achieved almost correct results but then I decreased the mesh scale (0.5 which led to 700 000+ element mesh) and the results were incorrect (similar to above).