analysis of naca2412 airfoil

gaurav · September 25, 2009, 19:32

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.

meon · September 26, 2009, 22:33

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.

gaurav · September 26, 2009, 23:54

Thanks a lot for your advice I shall definitely try it and get back to you.

September 25, 2009, 19:32	analysis of naca2412 airfoil	#1
gaurav New Member gaurav Join Date: May 2009 Posts: 9 Rep Power: 17	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.

September 26, 2009, 22:33	naca2412 16 degrees	#2
meon New Member Dr Peter Murdoch Join Date: Jul 2009 Posts: 3 Rep Power: 17	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.

Similar Threads
Thread	Thread Starter	Forum	Replies	Last Post
Multi-element airfoil analysis	CFD Rookie	Main CFD Forum	12	November 17, 2016 07:07
airfoil analysis	Hammam	CFX	10	June 22, 2007 14:18
Airfoil Mesh for DES Analysis - y+ Value	asd	Main CFD Forum	1	May 3, 2007 11:13
y+ for Airfoil Analysis	asd	Main CFD Forum	3	April 18, 2007 11:54
quasi steady analysis of 2d airfoil (pitching)	Alex	FLUENT	1	February 10, 2006 03:54

September 26, 2009, 23:54		#3
gaurav New Member gaurav Join Date: May 2009 Posts: 9 Rep Power: 17	Thanks a lot for your advice I shall definitely try it and get back to you.