Wing stall prediction.

aleix.de.toro · February 12, 2015, 15:57

Hi friends!

I am having problems with the results obtained when having a higher value of angle of attack. For a NACA 0012, when I increase until 20 degrees or more, the value of cl does not drop too much,i t remains near 1. I have tried with other airfoils and the values of lift coefficients don't go down.

Is fluent capable of predicting a stall when the angle of attack is too high?
What models do you use?

(I am trying with a 2d airfoil)

Thanks!

Farid · February 13, 2015, 14:43

This problem is better to be solved unsteady. Also, be sure that the mesh behind the airfoil (after separation point) is refined. Years ago at school, I remember a colleague solved this problem with fluent using Reynolds stress model and his results made sense.

February 12, 2015, 15:57	Wing stall prediction.	#1
aleix.de.toro New Member aleix de toro diaz Join Date: Dec 2014 Posts: 9 Rep Power: 13	Hi friends! I am having problems with the results obtained when having a higher value of angle of attack. For a NACA 0012, when I increase until 20 degrees or more, the value of cl does not drop too much,i t remains near 1. I have tried with other airfoils and the values of lift coefficients don't go down. Is fluent capable of predicting a stall when the angle of attack is too high? What models do you use? (I am trying with a 2d airfoil) Thanks!

Thread Tools	Search this Thread
Show Printable Version Email this Page	Search this Thread: Advanced Search
Display Modes
Linear Mode Switch to Hybrid Mode Switch to Threaded Mode

Similar Threads
Thread	Thread Starter	Forum	Replies	Last Post
Prediction of stall point	cfdeng	CFX	1	February 21, 2013 17:30
angle stall for a wing	Richard	CFX	5	July 3, 2008 02:49
Wing profile and stall	Jens	Main CFD Forum	0	June 26, 2007 10:42
Best CFD code for Airfoil Stall prediction	Narasimha Shastri	Main CFD Forum	0	June 15, 2005 02:00
Dynamic stall on circular wing	Anton Lyaskin	Main CFD Forum	1	November 4, 2002 07:47

February 13, 2015, 14:43		#2
Farid New Member Join Date: Apr 2014 Posts: 13 Rep Power: 13	This problem is better to be solved unsteady. Also, be sure that the mesh behind the airfoil (after separation point) is refined. Years ago at school, I remember a colleague solved this problem with fluent using Reynolds stress model and his results made sense.