If you give a presentation, please please get at least the orders in your formulas right.
In laminar flow drag is proportional to velocity. Lift is proportional to angle (of attack) times velocity for small angles. That's for lower mach numbers; at jet-cruise speeds compressibility of air becomes an important factor too.
Most airfoils are designed to bend the air and only accelerate it temporarily to get a higher pressure under the wing and a lower above. The global deceleration (before vs after the wing) is kept small, because of the design goal to keep drag low. (Action=Reaction: the drag force on the plane is the acceleration force on the air)