henra, 122
If I misunderstood 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.
Not at all and thanks for the patience. Shows just how much I (don't)
know about aerodynamics.
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.
Ok, if lift doesn't change significantly until beyond stall, but
the position does, other methods could be used, such as >1 pressure
transducers at critical points on the surface. If these were summed
differentially. the position of lift could be calculated, thus approach to
stall.
Going back to the strain gauge solution, assume that the lift position
produces a variable twisting moment to the wing ?. If so, this could
be measured to determine lift position.
Probably completely off the wall and i'm sure there's no shortage of
ideas, but it is Friday
...