|Vertical and horizontal stabilizer units on an Airbus A380 airliner|
An aircraft stabilizer is usually a tail surface assembly, including flight control surfaces, that provides longitudinal or directional stability and control. Depending on the context, "stabilizer" may sometimes describe only the front part of the tail assembly.
In the conventional aircraft configuration, stabilizers are positioned at the tail of the aircraft, and vertical and horizontal stabilizers are distinct elements. Longitudinal stability and control may be obtained with other configurations, such as canard, tandem wing or tailless aircraft. Other tail arrangements, such as the V-tail configuration, provide a combination of longitudinal (pitch) and directional (yaw) stabilization and control.
Some types of aircraft are stabilized with electronic flight control; in this case, fixed and movable surfaces located anywhere along the aircraft may serve as active motion dampers or stabilizers.
Longitudinal balance, stability and control 
A longitudinal stabilizer is used to maintain the aircraft in longitudinal balance, or trim: it exerts a vertical force at a distance so that the summation of pitch moments about the center of gravity is zero. The vertical force exerted by the stabilizer to this effect varies with flight conditions, in particular according to the aircraft lift coefficient and wing flaps deflection which both affect the position of the center of lift, and with the position of the aircraft center of gravity (which changes with aircraft loading). Transonic flight makes special demands on horizontal stabilizers, since the crossing of the sound barrier is associated with a sudden move aft of the center of lift.
An other role of a longitudinal stabilizer is to provide longitudinal static stability. Stability can be defined only when the vehicle is in trim; it refers to the tendency of the aircraft to return to the trimmed condition if it is disturbed. This maintains a constant aircraft attitude, with unchanging pitch angle relative to the airstream, without active input from the pilot. Since obtaining static stability often requires that the aircraft center of gravity be ahead of the center of lift of a conventional wing, a stabilizer positioned aft of the wing is then often required to produce negative lift.
Wing-stabilizer interaction 
The upwash and downwash associated with the generation of lift is the source of aerodynamic interaction between the wing and stabilizer, which translates into a change in the effective angle of attack for each surface. The influence of the wing on a tail is much more significant than the opposite effect and can be modeled using the Prandtl lifting-line theory; however, an accurate estimation of the interaction between multiple surfaces requires computer simulations or wind tunnel tests.
Horizontal stabilizer configurations 
Conventional tailplane 
In a conventional layout, the horizontal stabilizer, also named horizontal tail or tailplane, is a small horizontal wing located to the rear of the aircraft.
On many aircraft, the tailplane assembly consists of a fixed surface fitted with a hinged aft surface which is called an elevator. Trim tabs are then often used to relieve pilot input forces; conversely in some cases (small aircraft with all-moving stabilizers), anti-servo tabs are used to increase these forces.
Most airliners and transport aircraft feature a large, slow-moving surface named trimmable horizontal stabilizer which is combined with independently-moving elevators. The elevators are controlled by the pilot's yoke and primarily serve to change the aircraft’s attitude, while the whole assembly is used to trim (maintaining horizontal static equilibrium) and stabilize the aircraft in the pitch axis.
Three-surface aircraft 
Three-surface aircraft such as the Piaggio P.180 Avanti or the Scaled Composites Triumph and Catbird, the tailplane is a stabilizer as in conventional aircraft; the frontplane, called foreplane or canard, provides lift and serves as a balancing surface.
Some earlier three-surface aircraft, such as the Curtiss AEA June Bug or the Voisin 1907 biplane, were of conventional layout with an additional front pitch control surface which was called "elevator" or sometimes "stabilisateur". Lacking elevators, the tailplanes of these aircraft were not what is now called conventional stabilizers. For example, the Voisin was a tandem-lifting layout (main wing and rear wing) with a foreplane that was neither stabilizing nor mainly lifting; it was called an "équilibreur" ("balancer"), and used as a pitch control and trim surface.
Canard aircraft 
In the canard configuration, a small wing, or foreplane, is located in front of the main wing. Some authors call it a stabilizer or give to the foreplane alone a stabilizing role, although as far as pitch stability is concerned, a foreplane is generally described as a destabilizing surface, the aft surface being the stabilizing one as for every aircraft configuration.
In a stable canard aircraft, the wing acts as the stabilizer. In naturally unstable aircraft, the canard surfaces may be used as an active part of the artificial stability system, and are sometimes named horizontal stabilizers.
Tailless aircraft 
Tailless aircraft lack a separate horizontal stabilizer. In a tailless aircraft, the horizontal stabilizing surface is part of the main wing. Longitudinal stability in tailless aircraft is achieved by designing the aircraft so that its aerodynamic center is behind the center of gravity. This is generally done by modifying the wing design, for example by varying the angle of incidence in the span-wise direction (wing washout or twist), or by using reflexed camber airfoils.
Directional stabilization and control 
"Directional (or yaw) stability is usually provided by the fin and rudder together forming a total surface", the vertical stabilizer. Directional control is obtained with the use of the rudder, a movable surface at the rear of the fin. Less commonly, the whole fin surface is pivoted for both stability and control. Yaw stability makes aircraft tend to turn into gusts, rather than being deviated by them.
Tailless directional stabilization 
Although the use of a vertical stabilizer is most common, it is possible to obtain yaw stability on an aircraft with no discrete vertical stabilizer.
Wing sweep, for example on the Rogallo wing often used for hang gliders, provides a restoring yaw moment when the aircraft is rotated in yaw (the outer wing producing more drag than the inner wing). Electronic flight controls might increase yaw stability through the use of differential air braking, as on the Northrop Grumman B-2 flying wing. Fuselage geometry, engine nacelles and rotating propellers all influence lateral static stability.
Combined longitudinal - directional stabilization and control 
On some aircraft, horizontal and vertical stabilizers are combined in a pair of surfaces named V-tail. In this arrangement, two stabilizers (fins and rudders) are mounted at 100 - 120° to each other,[note 1] giving a larger horizontal projected area than vertical one as in the majority of conventional tails. The moving control surfaces are then named ruddervators.[note 2] The V-tail thus acts both as a yaw and pitch stabilizer.
Although it may seem that the V-tail configuration can result in a significant reduction of the tail wetted area, it suffers from an increase in control-actuation complexity, as well as complex and detrimental aerodynamic interaction between the two surfaces. This often results in an upsizing in the total area that reduces or negates the original benefit. The Beechcraft Bonanza light aircraft was originally designed with a V-tail.
Others combined layouts exist. The General Atomics MQ-1 Predator unmanned aircraft has an inverted V-tail; while the LearAvia Lear Fan had a Y-tail. All twin tail arrangements with a tail dihedral angle will provide a combination of longitudinal and directional stabilization.
See also 
Specific stabilizer/tail configurations 
- Canard configuration
- Three-surface configuration
- Tailless configuration
Components of stabilizers 
- Roskam, Airplane Design, part III Empennage - D. Stinton The design of the aeroplane, Longitudinal stability - Hoerner Fluid Dynamic Lift - Ilan Kroo, Aircraft Design. In stability considerations (tail sizing, tail area, stabiliser volume coefficient), authors always deal with the whole unit, that includes elevators. "Horizontal tail" or "tail" terms are generally used in lieu of "stabilizer".
- Daroll Stinton, The design of the aeroplane, "Longitudinal balance (trim)".
- Phillips, Warren F. (2010). "4.1 Fundamentals of Static Equilibrium and Stability". Mechanics of Flight (2nd ed.). Hoboken, New Jersey: Wiley & Sons. p. 377. ISBN 978-0-470-53975-0. "When the controls are set so that the resultant forces and the moments about the center of gravity are all zero, the aircraft is said to be in trim, which simply means static equilibrium"
- W.H. Phillips, A Career at NASA Langley Research Center, Chap.4, Flying Qualities
- Phillips, Warren F. (2010). "4.2 Pitch Stability of a Cambered Wing". Mechanics of Flight (2nd ed.). Hoboken, New Jersey: Wiley & Sons. p. 381. ISBN 978-0-470-53975-0. "For an airplane to be statically stable in rotation, any disturbances in roll, pitch or yaw must all result in the production of a restoring moment that will return the aircraft to the original equilibrium state."
- Phillips, Warren F. (2010). "4.3 Simplified Pitch Stability Analysis for a Wing-Tail Combination". Mechanics of Flight (2nd ed.). Hoboken, New Jersey: Wiley & Sons. p. 391. ISBN 978-0-470-53975-0.
- "Horizontal stabilizer - elevator", The Beginner's Guide to Aeronautics (NASA Glenn Research Center), Sep 13 2010
- Gérard Hartmann (05.12.2003), "Les hydros Farman" (PDF), Dossiers historiques et technique aéronautique française, "le stabilisateur avant sera supprimé en cours d'année ("the front stabilizer will be removed during the year")"
- Gabriel Voisin, Mes 10.000 cerfs-volants (My 10,000 kites), page 166: "et je m'apprêtais à tirer sur mon équilibreur... puis il braqua son équilibreur vers la montée."
- Garrison, P (December 2002), "Three's Company", Flying 129 (12): 85
- "Parts of Airplane", The Beginner's Guide to Aeronautics (NASA Glenn Research Center)
- Horizontal stabilizer - elevator, NASA, "On some aircraft, the pitch stability and control is provided by a horizontal surface placed forward of the center of gravity"
- eg In AIR International May 1999, p.311, Hoerner and Borst, Fluid Dynamic Lift, page 11-29, and Page 11-33 Delta canard, NASA TM 88354, A look at handling qualities of canard configurations, p. 14 and Kundu, Aircraft Design, Page 92,
- Phillips, Warren F. (2010). "4.6 Simplified Pitch Stability Analysis for a Wing-Canard Combination". Mechanics of Flight (2nd ed.). Hoboken, New Jersey: Wiley & Sons. p. 425. ISBN 978-0-470-53975-0. "…it is the main wing and not the canard that provides stability for the wing-canard configuration."
- AIAA/AHS/ASEE Aircraft Design, Systems and Operations Meeting: ... - Volume 2 - Page 309, "Pitching-moment results show the stabilising effect of the wing and the destabilizing effect of the canard."
- F.H. Nichols,The Effects of Wing Vertical Location and Vertical-tail Arrangement on the Stability Characteristics of Canard Airplane Configurations, page 9, "The body also produces a substantial destabilizing component which is adequately balanced by the large stabilizing effect of the wing."
- The X-29 ... while its canards — horizontal stabilizers to control pitch — were in front of the wings instead of on the tail" 
- Theory and Practice of Using Flying Wings, Apogee Components
- Notes on the stability and control of tailless airplanes, Jones, Robert, naca-tn-837, 1941
- Daroll Stinton, The design of the aeroplane, lateral and directional stability and spinning
- Barnard, R.H.; Philpott, D.R. (2010). "10. Aircraft control". Aircraft Flight (4th ed.). Harlow, England: Prentice Hall. p. 271. ISBN 978-0-273-73098-9.
- Barber, Horatio, "Chapter II - Stability and Control", The Aeroplane Speaks (Electronic Text Center, University of Virginia Library)
- Sweetman, Bill (2005). Lockheed Stealth. North Branch, Minnesota: Zenith Imprint. p. 73. ISBN 0-7603-1940-5.
- Phillips, Warren F. (2010). "5 Lateral Static Stability and Trim". Mechanics of Flight (2nd ed.). Hoboken, New Jersey: Wiley & Sons. ISBN 978-0-470-53975-0.
- Raymer, Daniel P. (1999). "4.5 Tail Geometry and Arrangement". Aircraft Design: A Conceptual Approach (3rd ed.). Reston, Virginia: American Institute of Aeronautics and Astronautics. p. 78. ISBN 1-56347-281-3.
- Phillips, Warren F. (2010). "5.5 Effects of Tail Dihedral on Yaw Stability". Mechanics of Flight (2nd ed.). Hoboken, New Jersey: Wiley & Sons. p. 533. ISBN 978-0-470-53975-0.
- Aircraft-related terminology
- Talay, Theodore A. (27 January 2005). "Introduction to the Aerodynamics of Flight – Stability and Control". NASA History Division. Langley Research Center. Retrieved 21 April 2013.
- "Dynamic Longitudinal, Directional, and Lateral Stability", Centennial of Flight (US Centennial of Flight Commission)