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October 25, 2010, 16:46 |
Determining Stall Angle of 2D Airfoil
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#1 |
New Member
Active Aero
Join Date: Oct 2010
Posts: 5
Rep Power: 15 |
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. |
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