I'm trying to analyse the relationship between the angle of attack and lift coefficient of a wing profile I tested. However, I am finding that the data shows that the wing hasn't stalled by the time it reaches an angle of 25 degrees, whereas I am under the impression that a wing usually stalls around 15 degrees. I cannot recall where I have heard it, but I am under the impression that one of the reasons the F-18 is capable of high AoA flight is because of the "surfaces" around the cockpit:
Is that correct? Is high AoA associated with smaller wing width and high chord length?
Also, this is the data I've gathered. I tested the same wing at three different airspeeds. Sorry about the text being in Danish.