I'm projecting a wing in XFLR5. The lift at the tip of the wing looks like it's dropping very quickly close to the stall angle, so I think there may be wingtip stall, however, is there any way I can confirm that? I thought about comparing the lift coefficient of the wing with the maximum lift coefficient of the airfoil, and If the local lift coefficient is bigger than the maximum airfoil lift coefficient, I can conclude that region is stalling. Is this thought process correct, or is there any other analysis I could make? If so, which Reynolds number should I use to acquire the airfoil lift coefficient, should I just consider the aircraft speed in the formula?
Here's the image of the lift distribution, if it's useful having a look at it: