Calculating Twist Angle of T-Tail Plane

[unluckystuden]

T-Tail moments??

Hey,
I've got a problem of a T-Tail plane that has an upwards force acting on the right side of the horizontal tail, and a downwards force acting on the left... to find the twist angle of the fuselage(assuming the main wings stay fixed) do you use a moment from the horiz. tail acting at the top of the vertical tail? And how do you convert this to torque?
Cheers,

 

[viscousflow]

For first pass estimation you'll need a few assumptions.

Assuming:
-The stabilators do not deform drastically under loading
- The fuselage shape is cylindrical

You can simply find the torque exerted on the tail about the Reference Line and assume this transmitted up to the point in question.