I’ve been studying Pilots Handbook of Aeronautical Knowledge FAA-H-8083-25B and on p 5-17 they talk about thrust line and stability. Can someone explain why the moment changes when thrust is applied?

Power or thrust can also have a destabilizing effect in that an increase of power may tend to make the nose rise. The aircraft designer can offset this by establishing a “high thrust line” wherein the line of thrust passes above the CG. [Figures 5-26 and 5-27] In this case, as power or thrust is increased a moment is produced to counteract the down load on the tail. On the other hand, a very “low thrust line” would tend to add to the nose-up effect of the horizontal tail surface. Conclusion: with CG forward of the CL and with an aerodynamic tail-down force, the aircraft usually tries to return to a safe flying attitude.

Figure 26 Figure 27


4 Answers 4


There is a general rule: don't trust "Pilot's Handbooks" when they talk about aerodynamics. More often than not, they are full of misconceptions and, at best, oversimplifications. In your quote, for example, the conclusion has nothing to do with the preceding text.

But the question is fair. Thrust line can affect stability, but we need to define what exactly we understand by that.

Stability as such is a negative reaction to a disturbance: a disturbance of a particular defined kind must cause a reaction which negates the original disturbance. Usually, we restrict the analysis to relatively small disturbances, when reactions are more or less linear.

Longitudinal stability, in a broad sense, describes any longitudinal motion. For airplanes this involves pitch or speed. (Altitude is a different axis and even a different frame, although we'll need to consider it in some cases). These are linked but different motions, and we can talk about them separately to some extent. It just happens that for most airplanes, the characteristic times of these angular vs linear motion is so different that we can very well analyse them independently. The heavier the airplane (and/or higher its wing loading), the better it holds. Even for GA airplanes it's still largely true.

In a strict sense, when aircraft designers (but not pilots) talk about "longitudinal stability", they mean the short-period pitch stability, or more accurately, angle of attack (AoA) stability. This means that when AoA is disturbed (by a gust or control input), a moment immediately arises that counteracts this AoA change (which is done via pitch change).

The mechanism behind AoA stability involves purely aerodynamic moments/forces. (The explanation involves the concepts of neutral point and moment derivatives). Notably, it does not involve thrust nor airspeed. Both of them change too slowly compared to AoA/pitch and so play practically no role in longitudinal stability per se.

But when it comes to airspeed stability, with which pilots are more intuitively familiar, the situation is different. Airspeed stability is linked to AoA stability via an indirect mechanism that Robert already roughly described in his answer: "increased thrust, increased speed, increased lift, plane rises vertically, vertical "up" pushes tail down, pitch changes". The important result is that a statically stable (read: AoA stable) aircraft will also be stable in speed. But even that holds only if drag doesn't grow faster than lift; that is, on the front side of the power curve. (Pilots know it very well). At high (but pre-stall) AoAs, the airplane will remain stable in AoA but will become unstable by speed.

Technically, this is still speed stability, not thrust stability. We are not concerned how airspeed changed: thrust, gust, dive, whatever. A statically stable airplane will try to pitch up and climb as a response to increased airspeed, slowing down as a result.

But when we analyse speed changes as a specific result of thrust changes, other factors come into play. Namely, apart from speed, changing thrust can disturb the moment balance of the airplane. In general, multiple effects can be important here, not only the location of line of thrust with respect to CG, but also with respect to 'centre of drag'; and the changed slipstream may cause aerodynamic changes. Either way, it may happen that these extra moments may augment or negate the natural tendency that comes from AoA stability.

For simplicity, let's analyse a few obvious cases of reaction to increased thrust (leaving everything else unchanged, particularly trim).

  • Thrust is in line with CG. The airplane will start to climb (or reduce descent) and will settle on the same AoA and roughly the same speed.

  • Thrust line below CG (the case of most airliners with underwing engines). This will produce an added pitch-up moment, which will cause the airplane to slow down more than necessary, despite the added thrust! This is an unstable condition. It can be particularly nasty in go-around situations. How do we fly it? Luckily, unlike AoA, the changes are slow enough for pilots (let alone autopilots) to react with active trim changes.

  • Thrust line above CG. This is the opposite of the above and, in moderate amounts, can have stabilising effect and easier trim changes. The airplane will settle at a higher speed, which is presumably what the pilot wants (despite the "power controls altitude" mantra). When the line is too high, the airplane may even descend and accelerate more than necessary, until the aerodynamic moment balances out the thrust moment, but overall the condition is stable. (Note that in most cases thrust starts to fall with increased speed, which helps to find the balance).

As a conclusion:

  • In a strict sense, line of thrust (and thrust as such) does not affect longitudinal stability per se; that is, the AoA stability.

  • However, it does affect airspeed stability, which many pilots understand as longitudinal stability.

  • It certainly affects trim changes, which, again, pilots perceive as a measure of longitudinal stability (not entirely without reason).

  • 1
    $\begingroup$ "The important result is that a statically stable (read: AoA stable) aircraft will also be stable in speed." May I disagree? Speed stability disappears at high angle of attack, on the back side of the power curve. While a statically stable aircraft will return to its old angle of attack, it will not return to its old speed when flown below minimum power speed because drag increases when the aircraft slows down further. $\endgroup$ Commented Nov 15, 2018 at 19:21
  • $\begingroup$ You are right, of course; I was just thinking about the 'normal' situation. I'll add a note. $\endgroup$
    – Zeus
    Commented Nov 15, 2018 at 23:08
  • $\begingroup$ "The important result is that a statically stable (read: AoA stable) aircraft will also be stable in speed ." That's not accurate. In transonic regime, AOA stability does not guarantee speed stability. That's why designers assess speed stability rather than AOA stability in detailed design and certification. $\endgroup$
    – JZYL
    Commented May 8, 2020 at 14:44
  • $\begingroup$ True, but it already gets too complicated for those who learn by 'pilots handbooks'... $\endgroup$
    – Zeus
    Commented May 9, 2020 at 15:24

You have two different questions.

Question 1

Can someone explain why the moment changes when thrust is applied?

The graph below illustrates the forces from a propulsor and its relative location to the airplane CG. As illustrated, the thrust line is below the CG. Therefore, as power is increased, more thrust is generated, and you get a nose-up moment.


Image ref: Etkins, Dynamics of Flight

Question 2

How does the line of thrust affect longitudinal stability?

This is a much more interesting question. The explanation below may be a little dry.

a. Longitudinal stability

Longitudinal stability, by the letter of the law, is defined by whether increasing elevator control force is needed to change and maintain an airspeed, and whether the aircraft returns to the same airspeed with elevator released. From an engineering perspective, it can be expressed as a single criterion (see Ch.6.5, Etkins, Dynamics of Flight):


where $C_m$ is the total pitching moment coefficient about the CG and $C_L$ is the lift coefficient of the airplane. This expression states that, with a constant stick force, the pitching moment must be nose down when lift increases from the trim point (i.e. airspeed decreases from trim speed), and vice-versa.

b. Thrust line effect

Now let's look at the pitching moment contribution from a propulsor ($C_{m_p}$):

$$C_{m_p}=C_T\frac{z_p}{\bar{c}}=\frac{T}{1/2\rho V^2S}\frac{z_p}{\bar{c}}$$

where $C_T$ is the thrust coefficient, $\bar{c}$ is the reference chord length, $T$ is thrust, $\rho$ is air density, $V$ is airspeed, $S$ is reference area, $z_p$ is the thrust line offset as shown in the picture above.

To keep matter simple, I'm going to assume that:

  1. We are dealing with a jet engine here such that the thrust stays constant (similar overall conclusion is drawn for a constant power propeller; for detail, see Ch.3.4 of Etkins, Dynamics of Flight) and,
  2. Lift is equal to weight such that:


With a straightforward differentiation with respect to $C_L$, we get:


As you can see, the sign of this quantity is dependent on the thrust line offset. A positive offset (i.e. thrust below CG) provides a destabilizing effect ($\frac{dC_{m_p}}{dC_L}>0$), whereas a negative offset (i.e. thrust line above CG) provides a stabilizing effect.


Figure 5-26 is good example of the result of applying a torque (F x lever arm) around the center of gravity. The effect is the same as applying aerodynamic torque, you get rotation. This is why an engine mounted "through" the CG will not have this effect. It should be noted that drag effects are ignored in this question, so we may consider 5-26 as the result of a CHANGE in THRUST.

EDIT: UPDATE: (keeping reading, keep learning)

The thrust line is actually balanced with center of frontal drag. Literature probably should be worded as such. The concept that all thrust torques rotate around the CG may be better defined as the net thrust/drag torque.

Thrust line interacts proportionally with tail down force as velocity increases (from more thrust), which is why nose down thrust angle is built into engine mount to increase pitch stability. We also may be learning that "positive static stability" (setting CG forward/down force on tail) may not be needed if directional stability is adequate, and may in fact introduce unwanted pitch up tendencies that require a larger tail to correct (or more trimming).

Figure 5-27 applies torque to the CG, indirectly, as follows: increased thrust, increased speed, increased lift, plane rises vertically, vertical "up" pushes tail down, pitch changes. Opposite for reducing thrust. This particular example has cruise (power and trim) as no effect. So we may consider 5-27 as a result in a CHANGE in AIRSPEED, resulting from change in thrust.

Fortunately, the manufacturer, through experience, will mount the engine (usually a few degrees down, and a little right) to offset these effects as well as left turning tendency.

In practice, one counter-acts these effects with the elevator, and re-trims once the speed desired by changing the throttle is reached.

For new pilots, one might think using your elevator also has an effect on your longitudinal stability too, but no, please do not worry about this.

Minor changes in throttle, as in setting up a landing, do not cause noticeable changes in pitch.

  • $\begingroup$ Are those things really a matter of stability, or trim? $\endgroup$ Commented Oct 13, 2018 at 3:31
  • $\begingroup$ Since in reality we do not go around constantly changing our thrust, the effect (academicly) is a change in pitch (there for destabilizing pitch). Once throttle is changed, we trim for our new speed. A good example of this is transitioning from climb out to cruise. We reduce pitch, reduce power (speed increases to around 100 knots from 70), hold desired altitude with elevator, then trim for cruise. It's SOP. $\endgroup$ Commented Oct 13, 2018 at 3:43
  • 1
    $\begingroup$ Pitch (elevator) controls speed, power controls altitude. Pilot controls pitch and power. Don't over think it. $\endgroup$ Commented Oct 13, 2018 at 12:46
  • $\begingroup$ @quiet flyer has a good point. It can be said that this is a matter of trim rather than that of stability. It is not over-thinking; on the contrary, the 'elevator controls speed' is over-simplification. I tried to explain it in my answer. $\endgroup$
    – Zeus
    Commented Oct 16, 2018 at 8:29
  • $\begingroup$ The point here seems to be that "high thrust line" or angling thrust down makes for a more pitch stable design in regards to thrust, maybe more so than (or in addition to CG ahead of CL). I would agree the wording could be improved. And discussion with experienced people certainly helps see other points of view. Maybe they write it stupid to get us to talk. $\endgroup$ Commented Oct 16, 2018 at 13:58

Just to add something to the already given answer and to what is stated in the pilots handbook.

Line of thrust is definitely not the whole story about the relationship between thrust and pitching moment. Actually it is only ⅓ of the whole story.

Indeed a propeller modifies the pitching moment via two other effects which are as important as the line of thrust but which are normally omitted.

  1. A propeller basically produces thrust accelerating the airflow behind it (aka induced velocity). This airflow with increased speed (dynamic pressure) washes over the wing and impinges on the tailplane. The effect on the wing is to increase its pitching moment while the effect on the tailplane is to increase its effectiveness due to the higher dynamic pressure. The net effect of those two phenomenon is in general a nose-up moment which increases with the thrust.

  2. Whatever the angle of the airflow investing the propeller is, the propeller tends to straighten the airflow behind it and align it with its axis, as depicted schematically in the following picture¹: propeller normal force As usual, due to Newton's third law, if the propeller bends the airflow downward, then the airflow reacts kicking the propeller upward. This reaction force is termed normal force $F_p$, it is proportional to the thrust and it goes upward for positive AoA. And it obviously creates a nose-up pitching moment.

To summarize, a propeller not only creates a thrust but creates a pitching moment as well. The direction (nose-up or nose-down) of this pitching moment depends on the net effect of the line of thrust plus the effect just described in 1. plus the effect in 2. The magnitude of this pitching moment is proportional to the thrust generated by the propeller, being it bigger for bigger thrust.

¹ from Wikipedia, modified by me


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