Wing loading in conceptual design Is it possible to have a minimum wing loading at climb segment of our design aircraft (air superiority)?
Which segment would have minimum wing loading i.e. climb, take off, cruise, instantaneous turn, sustained turn, etc?
From lowest to highest wing loading:


Climb: if a fixed wing plane and the nose is pointing up, some of the vertical force must be generated by the thrust.
Cruise: the lift must only compensate for the weight.
Inducing a turn: the rolling velocity has very little effect on wing loading.
Take-off: a slight positive g-loading during the nose-up motion.
Sustained turn: up to the maximum design load factor. 2.5g for passenger aeroplanes, up to 9g for fighter jets, with a proportionately greater wing loading that that in cruise.