Originally Posted by
syseng68k
Hyperveloce, 105
Have been thinking about something similar, but in relation to wing loading
as an extra parameter input for the calculation of lift. For the control
surface case, this could be instrumented via strain gauge type transducers,
one would think, near the control surface root.
syseng68k
If I misnderstood what you wrote I apologize upfront, but the wing loading in a stable stall will be roughly the same as in level flight, i.e. 1g.
The main difference would be the exact point where the lift is applied. In a fully stalled wing this will move from the Quarter Chord to the middle of the chord, so the moment on the wing might change a bit but the vertical force won't change much.
In a really deep stall on the other hand it might indeed work as the force on the wing it will decrease a significant bit as the fuselage will take over some part of the lift. In the attitude of AF it might contribute ~30%, so it could work to some extent but only at a point where it might be too late.