Originally Posted by ChristiaanJ
But to get back to the original question, I'm still convinced that in a "typical" aircraft in a "typical" steady climb, the extra force needed to compensate W/W*cos(climbangle) i.e., a slightly higher vertical force, comes for 90% from a slight increase in "lift", by means of a slightly higher AoA.
a) The required net vertical force generated by T, D and L will still be the same as in level flight: W.
b) I don't know where you get W/W*cos(climb angle) from. It's the same thing as cos(climb angle) BTW... and why would you ever need to compensate a plain cosine?
c) You saw all the math above, giving you L = W*cos(climb angle). If you still think lift needs to increase, perhaps you should point out the error in the calculations... ?