Determining Stall Angle of 2D Airfoil
 

Hi Guys,

I am fairly new to the FLUENT software. I have a GAMBIT 2D Mesh using Quad Map and I have successfully imported it into FLUENT. It has recognized my boundary conditions that I had set in GAMBIT.

My question is; is there a simple way (simple is probably the wrong word) but is there a way to determine the airfoil's stall angle without having to simulate the flow for every degree and then just picking the highest. Or is there a way to tell FLUENT to test all angles between a range of lets say 0degrees to 25 degrees?

A second question I have is that I tried a variety of angles by setting the flow to have x and y components, but my coefficient of lift kept increasing. From another software (Xfoil) we have previously determined that the stall angle was around 12 degrees. With Fluent I tried 0, 5, 10, 15, 20 and the coefficient of Lift kept increasing between each degree. I am not entirely sure how it could have, so test it I tried 30 degree KNOWING that the coefficient should have gone back down, but I got an even BIGGER answer. I was wondering if anyone knew what sort of model I should be running this through? I tried reading the User's Guide and the Theory Guide and I chose my models based on that. The airfoil is a LOW speed airfoil <300km/h so I couldn't use inviscid modelling...

Any help for both of these questions would be greatly appreciated!

Thanks in advance,

A.A.F.

Maybe you should try k-omega models for flow sweperation.

There are many methods to predict the stall angle of a foil section. For some particular sections, some test results can be used, such as NACA series. Wing Section Theory by Abbot is a best reference book with many test results. Also there are some reference books or reports for foil sections.

Thanks for your help, so you are saying that FLUENT the software itself cannot simply run a test where it tries each and every angle as a sweep from lets say -30 to +30 degrees and then determines the stall angle based on the output comparison from each angle.

So if I were to find an outsiders information about the stall angle of a certain wing, then I could use FLUENT to test the results for set angle. Ok

Thanks again guys,