I am designing a scale propeller for small UAVs and I have computed blade twist distribution for the blade airfoil sections. While I was modelling the propeller I have set the angles to twist about the trailing edge of each section so that this point is collinear. However, the final result looks a bit weird. I would like to ask whether I have to consider any other point of the airfoil to set for the twist angle (Maybe leading edge or C.G). Below is a screenshot for the final model.
You should be twisting the profile chord, like in the picture. Why is your tip so small, that is where most thrust is created.
I don't think performance will change, wether you use trailing edge or leading edge or somewhere in between reference for twisting. What matters is radial airfoil morphing along radius and common sense mass distribution around centripetal constraints. following those you wont come up with a straight twisting reference line. Have a look at APC model propellers site, it may help.