I think you're getting confused with the Coefficient of lift and a numerical value. Are you talking about the maximum upward force of lift in Kg? LIFT (available) is always greatest at Max AoA of the wing. Sure you decrease AoA with airspeed to stay SaL, but the question is 'When is the lift greatest'. With reduced AoA the Lift produced at cruising airspeed is the same as with a high AoA at slower airspeed (still SaL). Therfore the lift force (in Kg) will be greatest at high AoA and high airspeed.
Imagine you are cruising at 2000' at 60 kts, AoA is at 16° and the LIFT produced is say 1100Kg (equal to aircraft weight whatever that is, so you're flying SaL). Now you accellerate to 100Kts but keep AoA still at 16°, now the LIFT produced is say 2000Kg, and you'll climb. Now accellerate to 120 Kts, and the LIFT produced could be 2300 Kg and you'll climb faster.
Therefore the wing will ALWAYS produce most lift force (in Kg) that it can (at that altitude and that airspeed) at max AoA. If you travel faster it produces more lift for the same AoA, if you travel slower it produces less lift for same AoA. This is the same for all altitudes, air densities,temperatures etc. Of course at higher altitude the wing will not be capable of producing as much lift force (in Kg).
Lift=1/2*CL*density*vsquared
This formula should read 'Max possible lift force in Kg generated by the wing' and if you look at it, it says that lift (force in Kg) will be greatest with max coefficient of lift (ie max AoA, around 16°), in most dense air, and at highest velocity. This phase of flight is normally straight after rotation, (ignoring ground effect) when you're climing out at best rate of climb speed. You are attaining max forward speed that you can (for that AoA) and AoA is very near max, with density also at a max.
Cheers
EA