ft, did you not replicate with
with what I wrote in the previous post:
?

We can produce all sorts of fancy formulae (which really won't mean anything to anybody without a diagram!), but the answer will be- AoA will be in proportion to Cos climb angle. A 15 degree climb will have .97 of level flight lift- you know it, I know it- I feel it in me bones!

Rainboe, yes, I was replying to you. AoA will typically be a few degrees negative in a vertical climb rather than zero, due to camber. Fuselage pitch relative to the airflow will be another few degrees more negative due to angle of incidence.

Of course this means I goofed earlier. AoA in a climb won't be given by

AoA_climb = AoA_level*L_climb/L_level

at all, even though the relationship is essentially linear.

(AoA_climb-AoA_zero_lift) = (AoA_level - AoA_zero_lift)*L_climb/L_level

should hold more or less true though!

As for diagrams, you have them earlier in this thread. In addition, this is rather obvious to a lot of people without diagrams so you're making a rather broad statement there. After all, this is only the basic T/W/D/L diagram.

It seems we've now dealt with the original question, and we've all agreed lift and AoA decrease in a steady climb, even if only very little for small climb angles in a 'conventional' aircraft.

So we're now dealing with Rainboe's pet situation, a steady vertical climb.
Admittedly, at first sight we are just talking T=W+D+L, but since none of those vectors point in exactly the right direction, another diagram may be called for?

CJ