Ok,  here are a couple of thoughts on improving the elevator model; as
always comments and suggestions are welcome, flames will be ignored

@ line 220 or so  of FGAerodynamics add:

 alphat = alpha + tailincidence - downwash;  // alpha fro the tail

for now we'll assume no flying tails just a normal hinged elevator, so the
incidence is fixed and specified in the aircraft xml file.  To calculate
the downwash we use the following formula

downwash = 2 * CL(wing) / (pi * AR)

where AR is the aspect ratio of (cbar*cbar)/Sw, but cbar is actually a
variable dependent on the wing/flap configuration; so we need to
recalculate cbar whenever the configuration changes and, at some point,
we'll need to consider any delta cbar as a time dependent variable based
on flap extension/retraction rates.

Obtaining CL and pi is trivial, so the task at hand is the best way to
calculate the aspect ratio - something that only has to happen when the
wing configuration changes.

So once we have the alpha at the tail and assuming a trim tab set to some
value the stick free elevator (aka floating) becomes

elev_float = - ((b1*alphat + b3*trim)/b2*elevator) * alphat

where b1 = (partial) Ch with respect to (partial) alphat
and
b2 = (partial) Ch with respect to (partial) elevator
and
b3 = partial Ch with respect to (partial) trim

All that remains is to calculate the elevator balance position where Cm =
0; i.e., steady state flight aka a trimmed aircraft or

elev_float = elev_balance

I'll stop here for now.  The next set of calcs would be to determine the
control force gradient to apply to the stick as it is moved from the
neutral (or zero stick force location).

Regards
John






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