|September 25, 2009, 18:32||
analysis of naca2412 airfoil
Join Date: May 2009
Posts: 9Rep Power: 7
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
I am using the roe scheme 3 order . Kindly suggest .
|September 26, 2009, 21:33||
naca2412 16 degrees
Dr Peter Murdoch
Join Date: Jul 2009
Posts: 3Rep Power: 7
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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