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analysis of naca2412 airfoil

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Old   September 25, 2009, 18:32
Default analysis of naca2412 airfoil
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gaurav
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Hi,
I am trying to analyse a 2-d model of a naca2412 Airfoil (cord length 1 meter) at an angle of attack of 16 degrees to calculate the coefficient of lift using "WIND-US" . But my solution never seems to converge. I have run about a 1,20,000 iterations yet it keeps oscillating consistently between 0.7 and 2.2. It keeps generating the same pattern.

I have the following conditions

pressure: 15.4 psi
temperature: 540 R
velocity: 0.2 Mach
angle of attack: 16 degrees
Laminar flow.

I am using the roe scheme 3 order . Kindly suggest .

Thanks.
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Old   September 26, 2009, 21:33
Default naca2412 16 degrees
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Dr Peter Murdoch
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Sounds like its stalling. 16 degrees is close to the stall angle.
Check the pressure plot on the upper surface at the chord positions 0.2 0.4 0.6 0.8.

If you really need to get this to solve try running it as a transient, start at 10 degree aoa and then slowly increase it.
That should do the trick.
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Old   September 26, 2009, 22:54
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gaurav
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Thanks a lot for your advice I shall definitely try it and get back to you.
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