# NACA 0012 lift and drag coefficient.

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 March 28, 2012, 20:32 NACA 0012 lift and drag coefficient. #1 New Member   Tan Join Date: Dec 2011 Posts: 10 Rep Power: 14 I am running ANSYS fluent simulation flow over naca 0012 airfoil. So far the lift coefficient is similar with the published papers. The problem is drag coefficient is different so much in term of value compared to published papers. I have check my mesh quality and boundary condition, it shows no problem. Any idea why drag coefficient is different ???

 March 28, 2012, 21:18 #2 New Member   Minjae Lee Join Date: Mar 2012 Location: South Korea Posts: 3 Rep Power: 14 you may check the tubulrence model. which turbulence model did you appplied? generally, S-A 1equation model predict the drag coefficient less than compare with published paper. I recommand to you T-SST 4equation turbulence model. if you solving 2 dimensional problem using about 300 surface nodes on the airfoil, that the drag coefficient is predicted less than 5% error.

March 28, 2012, 22:33
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Tan
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Quote:
 Originally Posted by leemj you may check the tubulrence model. which turbulence model did you appplied? generally, S-A 1equation model predict the drag coefficient less than compare with published paper. I recommand to you T-SST 4equation turbulence model. if you solving 2 dimensional problem using about 300 surface nodes on the airfoil, that the drag coefficient is predicted less than 5% error.
Reynolds number = 360,000
Is it laminar or turbulence flow??

March 29, 2012, 03:32
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Minjae Lee
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Quote:
 Originally Posted by Tom Lucius Reynolds number = 360,000 Is it laminar or turbulence flow??
The flow is fully turbulent flow when Re>2,300 in pipe flow for air. So I recommand to you that you need to apply the turbulence model especially transition-SST 4equation model. In addition, not only you have to making surface nodes more than 270 but also consider wall y plus.
(you can find the wall y plus information NASA hompage.)

March 29, 2012, 05:32
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Quote:
 Originally Posted by Tom Lucius Reynolds number = 360,000 Is it laminar or turbulence flow??
At this reynolds number the flow is transitional. E.g. at zero angle of attack transition to turbulent at this Re and this airfoil happens at about 80-90% of the wing chord. At angle attack 5deg it happens at about 25% of wing chord.

Using turbulence models in CFD-software without special user input will likely give very wrong results for drag at such reynolds number.

Truffaldino

March 29, 2012, 05:54
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Tan
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Quote:
 Originally Posted by truffaldino At this reynolds number the flow is transitional. E.g. at zero angle of attack transition to turbulent at this Re and this airfoil happens at about 80-90% of the wing chord. At angle attack 5deg it happens at about 25% of wing chord. Using turbulence models in CFD-software without special user input will likely give very wrong results for drag at such reynolds number. Truffaldino
Truffaldino ,

Sorry for my poor knowledge, how to determine which reynolds number is laminar or turbulent? I google it and cant find the knowledge i want. Any source for me to study?

I face problems in drag coefficient where it is different from the published papers.

 March 29, 2012, 06:40 #7 Senior Member     Join Date: Jan 2011 Posts: 249 Blog Entries: 5 Rep Power: 17 Hello Tom, Your question where the flow is turbulent and where is laminar is not an easy question: this is one of the difficult problems of fluid dynamics and the answer depends not only on reynolds number, but also on problem geometry, boundary condition and amount of free-stream turbulence. In your case flow is neither turbulent nor laminar, there will be a transition from the laminar to turbulent flow somewhere. In the above examples I have used XFOIL program to find the transition location: For instance, at zero angle of attack and Re=3.6E5 the flow is laminar at both sides of airfoil up to approximately 80% of the airfoil chord and it becomes turbulent after. For angle of attack 5 deg the flow is fully laminar at lower side of airfoil. At upper side it is laminar up to 25% of the chord and turbulent after. X-foil is so far the best software for analysing flows past conventional airfoils at low reynolds numbers: it is more accurate in predicting drag than RANS modelling. This program is free and easy to use. So, before using CFD software with RANS I reccomend you to run XFOIL analysys to have an idea what to expect, where to expect flow separation and reattachment, transition etc. Truffaldino

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