In straight-and-level unaccelerated flight there are two physical quantities that must cancel:

- force: 𝐹
_{L}= 𝐹_{W}+ 𝐹_{T} - torque: 𝑟
_{L}𝐹_{L}= 𝑟_{T}𝐹_{T}

- the length of the arm to the center of lift increases, thereby increasing the moment of lift
- the length of the arm to the center of tail force increases as well; however. since it was at a greater distance from the CG to begin with, it doesn't increase proportionally as much; thus, the moment induced by tail force increases less than the moment of lift does
- this induces torque pulling the wings up
- to counteract the torque an increase in tail downforce is required (i.e., yoke is pulled aft, elevator deflects upwards)
- to counteract the increased downward force now imposed by the tail, an increase in lift is needed (i.e., increase wing AOA by pushing the tail down, which requires even more yoke backpressure, induces more downward force which must be compensated even more, etc.)
- at some maximal point of forward CG, the wing cannot produce sufficient lift anymore (i.e., the critical AOA is reached) or the elevator cannot produce sufficient downward moment to counteract the upward moment of the wing

- the length of the arm to the center of lift decreases, thereby decreasing the moment of lift
- the length of the arm to the center of tail force also decreases; however, since it was at a greater distance from the CG to begin with, it doesn't decrease proportionally as much; thus, the moment induced by the tail force decreases less than the moment of lift does
- this induces a torque pulling the tail down
- to counteract the torque less tail downforce is now required (i.e., yoke is pushed forward, elevator deflects downwards)
- because of the reduced tail downforce, less lift is needed from the wings to compensate (i.e., decrease wing AOA by raising the tail, which requires even less yoke backpressure, reduces downward force even more requiring even less wing lift to compensate, etc.)
- at some theoretical maximal point of aft CG where it is even behind the center of lift, the elevator cannot produce sufficient upward moment to counteract the downward moment of the wing. In practice ???

The difference in lift and tail arms is a constant for the aircraft; we can further clarify these if we substitute as a parameter the ratio of the lift arm to this constant as:

Then, α = 0 represents some ‘extreme aft’ condition where CG has come to coincide with CL; in this case, lift exactly counteracts weight and the tail-down force required is zero. Conversely, α = 1 represents the ‘extreme forward’ condition where CG is forward at an equal distance from the wings as the tail is rear to it; now, the tail-down force must equal weight and the wings must therefore lift double the aircraft's weight.

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