Stall Angle not showing with highest AOA at 90 degrees also with respect to benchmark UAV aircraft given by flow 5 team, in L vs alpha graph & also for My aircraft also not showing any stall angle as I am increasing the aoa aircraft is not stalling

[AadarshGejage]

dear team, I have checked 2d analysis of airfoil suppose for clark Y airfoil it stalling in cl vs alpha at 15 aoa but when I am doing analysis for benchmark aircraft given by flow5 or xflr5 website, so when I checked by increasing AOA till 90 degrees still it is not showing stall for 3d Aircraft analysis, vice versa for my UAV my wings 2d Airfoil is stalling around 13 degrees but in reality for 3d Aircraft analysis when I am doing T1 at 19 ms or at any speed it is showing at 45 degree also my aircraft is not stalling what can be reason for this? I am adding images of benchmark aircraft L vs alpha polar and also the geometry view of benchmark aircraft for reference please check and let me know the reason


Fuse_test.zip
I have added benchmark aircraft file also for the reference

[Flying-Geek]

You are running an inviscid analysis, which cannot be used to predict stall. Remember that at its core flow5 is a potential flow solver, so predicting flow separation even with the viscous analysis is difficult and can often lead to misleading results.

Cheers,
Stefan

[AadarshGejage]

So, If I run viscous analysis also it seems the results are not that much perfect even stall is not happening, waiting for tech winder author comment as well. thank you, Stefan, for response

[AadarshGejage]

@techwinder waiting for your suggestion.