I am currently analyzing a wing with a maximum CL of 1.08 at an angle of attack of 15 degrees. I always thought that this is the point of stall. Stall occurs where the CL drops off with increased angle of attack. However this site claims that the stall occurs at an angle of attack of 9 degrees, much lower than the maximum CL angle.
Max CL = 1.08
Max CL angle = 15
Stall angle = 9
Doing further research I found that an individual defined stall as the angle where the pitching moment starts to decrease, which makes sense. I would like to confirm this and if true, would like to reference this from a trusted source. Can anyone give me a trusted source that backs this definition?
Kind Regards
Martin
I hope this conference paper be helpful
Conference Paper A CFD Database for Airfoils and Wings at Post-Stall Angles of Attack
Dear Martin Bachrodt ,
In fluid dynamics, a stall is a reduction in the lift coefficient generated by a foil as angle of attack increases.[1] This occurs when the critical angle of attack of the foil is exceeded. The critical angle of attack is typically about 15 degrees, but it may vary significantly depending on the fluid, foil, and Reynolds number.
https://en.wikipedia.org/wiki/Stall_(fluid_mechanics)
Regards, Shafagat
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