I thought this is what I said: "Airfoil at the root inherently has lower air speed and higher angle of attack "

As far as CAOA independent of airspeed, I guess I stand corrected. I mistook "insufficient lift" with "stall". An airplane wing "stalls" when it falls below certain airspeed, or so they say. It really just "reduces" lift and cause airplane to drop.

I am a novice when it comes to aerodynamics. I work as a mechanical engineer in a non-aero related industry. My resource comes from only aerospace course when I was getting my MSME, and some self study. I am guessing that an airfoil stalls when air separated at LE fails to converge at TE through laminar flow. A typical airfoil w/ 90 degree AOA will definitely stall upon any air speed. I am wondering for a symmetrical airfoil at 45 degrees AOA, does it generate any lift at a low airspeed, say 5 mph?

Some technical education would be enlightening!