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.

 

[NatSusan]

Hey there,

It sounds like you have a classic case of asymmetric T-Tail moments. In order to find the twist angle of the fuselage, you will indeed need to use the moment from the horizontal tail acting at the top of the vertical tail. This moment is essentially the force multiplied by the distance between the force and the point of rotation (in this case, the top of the vertical tail).

To convert this moment to torque, you will need to multiply it by the distance between the point of rotation and the point where the force is applied. This will give you the torque, which is essentially a measure of the force's effectiveness in causing rotation.

I hope this helps! Let me know if you have any other questions. Good luck with your T-Tail plane!