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.