# Axis of rotation of tail surfaces

In cases where complete tail surface rotates (be it horizontal, vertical or at angle) what should be preferable axis of rotation of surface.

• We don't need all these votes for closing a perfectly valid question of a new contributor. Jul 28, 2019 at 8:40
• @Koyovis The question is flagged as unclear what you're asking and it is indeed unclear to me what exactly the OP wants to know. If you understand, could you edit to clarify? Jul 28, 2019 at 10:05
• @Bianfable Why would we close the question though, and not simply ask for more info in a comment. Jul 28, 2019 at 12:13
• A legitimate question. While there is some engineering design discretion, there are practical limits to where along the chord line of the control surface the pivot point can be located. I'm voting to leave open. Jul 28, 2019 at 12:35
• @Bianfable It looks clear to me. Is there a particular thing about it you find unclear? Jul 31, 2019 at 1:03

A "preferable" solution depends on many factors, both in aerodynamics and in design/construction. There is no single best solution for all situations.

On slow(er) subsonic aircraft with reversible control, the main concern is to provide convenient force on the yoke/stick. For symmetric airfoils, which are common for tails, there is a point at 0.25 chord where the hinge moment will be zero for all the operational range of deflections. To provide some positive force, you'll want to put the axis slightly ahead of this point.

However, there is another problem: stability with relaxed controls. If you move the axis too much forward, making the surface 'weathervane' with the stream, you reduce the control-free stability. This is an important consideration because when you are flying 'hands off' on a well-trimmed airplane, this is exactly the situation you are in. With classic hinged elevators, this effect is already quite noticeable, but with all-moving tails, it can be extreme, up to the total loss of stability. On the other hand, obviously, if you put the axis aft of this 25% chord, you'll have an outright unstable configuration.

So the ideal situation for such airplanes is to have the axis at 25% chord, but to create positive control force with springs or with an anti-servo tab, like on PA-28:

$$\hskip 6cm$$
Source

For supersonic aircraft, the situation is somewhat different.

First, their control is typically irreversible: the actuators take all the load. This means that the control-free stability problem doesn't exist; and the actuators can potentially control high (or even negative) hinge moments.

Still, you don't want to oversize the actuators unnecessarily. In addition, many (older) supersonic aircraft allowed for fully manual or assisted control in case of hydraulics failure, so the aircraft still had to be flyable by hand.

This again puts the best hinge location near the 25% chord point.

However, the second difference is the fact that at supersonic speeds, this magic 25% chord point (called aerodynamic centre) moves to 50%. On top of that, the relative efficiency of control (per degree of deflection) reduces, and this is actually one of the main reasons of using all-moving surfaces on supersonic aircraft. This, obviously, creates enormous hinge moments.

To reduce them, we could move the axis a bit back. This may create negative moment at subsonic speeds, but if we have a full-authority hydraulic control, this may be the optimal solution. Some 4th-generation fighters seem to follow it.

The third difference is that supersonic tails are often highly swept back. How do you align the axis then?

$$\hskip 1cm$$

Again, there is no best solution for all cases. Aerodynamically and kinematically, the straight axis (on the left) is a bit better: it creates direct linear control. Structurally, it depends on how the stabiliser and the tail section are designed.

If there is a possibility to use a common shaft for both halves of the horizontal tail (which is typically true for T- and cruciform tails), this is a enormous advantage and it naturally leads to the straight axis. On the other hand, it is usually easier to integrate the shaft (or hinge points) along the spar of the stabiliser, which favours the swept axis for most swept tails.

• Your statement on reversible all-moving tail is correct. However, it's not a matter of where to place the hinge (assuming ahead of 1/4 chord). Rather, without an anti-servo tab, the stick-free neutral point moves to the wing AC! The tail might as well not be there. An anti-servo tab helps, somewhat, but now your HM is even worse. I think a reversible all moving tail is just not realizable.
– JZYL
Jul 30, 2019 at 23:44
• What do you mean 'not realizable'? What about PA-28? Now theoretically, it only matters whether the axis is ahead or behind the tail AC, yes, but in practice, given the friction and inertia, there is some margin, so the AC (25% MAC) remains a practical optimal hinge location. (Still, I'll add a clarification).
– Zeus
Jul 31, 2019 at 0:30
• Interesting. I don't think an anti-servi tab can restore the stick-free NP by much more than 10%. Does that mean it has a large trim drag while designing for field performance?
– JZYL
Jul 31, 2019 at 0:41
• I don't know; PA-28 feels quite stable. But why should it be large? In my understanding, the only way a reversible trimmable all-flying tail can work is to have the axis slightly ahead of AC. This makes aerodynamic trim work; and the stick-free stability must be provided by anti-servo. The 'weatherwaning' hinge moment per AoA of the tailplane itself is easily measured/calculated, and we can kinematically link the anti-servo to provide an exact same counter-moment, thereby fully restoring stick-free stability.
– Zeus
Jul 31, 2019 at 1:03
• Yes. But this is rarely significant for the tail. On the other hand, your effective deflection will be moderated by cos(axis_sweep), which can be very substantial.
– Zeus
Jul 31, 2019 at 2:30

Picture source

The axis of rotation of the F-16 stabilator can be seen on the picture. Design should be such that:

• The airflow attempts to bring the surface back to neutral from a deflection. Meaning: more surface aft of the hinge than before the hinge.
• The aerodynamic resistance moment is relatively constant, and of not too large of a magnitude. This can be achieved by choosing the hinge near a point where aerodynamic hinge moment is relatively constant, as function of angle of attack.

The most suitable axis of rotation would be the aerodynamic centreline, around 0.25 chord for:

• Symmetrical airfoils.
• Subsonic flow.
• Limited range of deflection.
• Zero sweepback angle.

For supersonic flow, the Centre of Pressure shifts aft and the aerodynamic centre of the surface is about 0.5 chord. For sweptback surfaces, there is relatively more area aft of the hinge line and the hinge should move aft.

• Thanks. Under what conditions we can/have to differ from this preferred choice. Jul 28, 2019 at 9:09