Calculated stall speed.

How does lift change with airspeed if a constant AOA and altitude are held? $($provide specific examples$)$

How does lift change with altitude if a constant AOA and airspeed are held? $($provide specific examples$)$

How do the required CL and AOA for your specific aircraft $($at a specific weight$)$ change with changes in airspeed? $($provide specific examples$)$

What happens if the required CL is larger than CLmax of your airfoil, and what speed regime is usually associated with that condition? Compare your main airfoil to a symmetric airfoil.