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February 12, 2015, 15:57 |
Wing stall prediction.
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#1 |
New Member
aleix de toro diaz
Join Date: Dec 2014
Posts: 9
Rep Power: 11 |
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! |
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February 13, 2015, 14:43 |
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#2 |
New Member
Join Date: Apr 2014
Posts: 13
Rep Power: 11 |
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.
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