Originally Posted by Lost

...the center of lift is always just that, the center of lift. I am not sure how you can include the stabilizer in the picture - the center of lift will show up somewhere about the MAC of the wing. I would LOVE to know how you can look at cg range and come up with the remark that at some point the *stabilizer* is responsible for some of the total lift force required.

Let me ask, do we agree that most (I say all) of the time, the stab is producing a down force? If yes, and you think at some point it produces a load supporting up lift, what happens right at the point where it transitions? Explain what you think stability will be like at that point? Or, what stability will be like if at any point in the flight will be like if the stab is actually lifting in the same direction of the wing? That would be one tough airplane to fly. I would think it would need a computer.

Your concepts of stability and control are far different than mine, and I am just asking for your explanation...