An outboard tail is a type of aircraft tail or empennage which is split in two, with each half mounted on a short boom just behind and outboard of each wing tip. It comprises outboard horizontal stabilizers (OHS) and may or may not include additional boom-mounted vertical stabilizers (fins). OHS designs are sometimes described as a form of tailless aircraft.
The outboard tail surfaces are positioned so that they interact constructively with the wingtip vortices to significantly reduce drag, without causing undue structural or handling difficulties.
An outboard tail is located outboard of the main wing tips. Although sometimes described as tailless, the outboard tail configuration differs from a tailless wing in that the horizontal stabilizer is discontinuous from the main wing surface, typically being set further back and requiring a short boom to support it. If the wing is swept, then the boom can be very short and the front of the tail may overlap the rear of the wing. The tail comprises outboard horizontal stabilizers (OHS) and may or may not include additional boom-mounted vertical stabilizers (fins).
A normal wing tip creates a significant trailing vortex, due to an upwash of air spilling up round it from underneath and then moving inwards towards the low pressure region above the wing surface. These vortices can carry away significant amounts of energy, thus increasing drag.
In the outboard tail configuration, the tail surfaces are positioned so that they interact constructively with the upwash behind the wing tips and, with careful design, can significantly reduce drag to improve efficiency, without reducing the handling qualities or adding unduly to the structural loads on the wing.
Compared to a tailless swept wing of similar overall span, the outboard tail has a greater moment arm than if it were attached directly to the wing, while the wing need not sweep back so sharply as to have undesirable side effects.
The outboard elevators can also be used as secondary ailerons, increasing the effective control area. This reduces the variation of loading on the wing during critical manoeuvres such as landing and allows a higher design loading for the wing. This in turn allows greater safety margins when landing.
Vertical tail fins traditionally provide directional stability and control. In outboard configuration they can also enhance airflow and contribute to overall efficiency, in a manner analogous to winglets.
The configuration was first developed during World War II by German designers Richard Vogt and George Haag at Blohm & Voss. In order to test the proposed control system, Škoda-Kauba adapted the V-6 design as the SK SL6 in 1944.
Blohm & Voss then incorporated the design into the P 208 pusher-engined fighter proposal. Although it was not taken up, modern analysis has shown that it would have been viable. B&V went on to produce a series of design studies and project submissions for similar jet fighters. These included the P 209.01, P 210 and P 212. B&V finally received an order for the P 215 all-weather fighter just weeks before the war ended, so it was never built.
During the late 1950s and early 1960s the principles of the outboard tail were re-investigated by NASA (formerly NACA) engineers, as a part of their research programme into design configurations for supersonic flight. They conducted analyses and wind tunnel model tests at both subsonic and supersonic speeds.
Burt Rutan at Scaled Composites became interested in the configuration for its potential as a variable-geometry stabiliser on a spaceplane. During atmospheric re-entry from space, the tail would rotate vertically to stabilise the plane, the rest of which remained horizontal but fell near-vertically. His first prototype, the Scaled Composites SpaceShipOne took to the air in 2003. It has since also flown on the improved SpaceShipTwo.
- Muller (2002)
- Darrenougue (2004)
- Pohlmann (1982) p.181
- J. A. C. Kentfield; "Flow Fields Around the Tails of Aircraft with Outboard Horizontal Stabilizers", AIAA 2006-860, 44th AIAA Aerospace Sciences Meeting and Exhibit, 9-12 January 2006: "Similarly, when the vertical stabilizer surfaces are mounted above the tail support booms, the inwash flow generated by the mainplane tip vortices results in the generation of horizontal aerodynamic lift forces acting, essentially, towards the aircraft center-line but also inclined forwards thereby producing a small thrust that tends to cancel the induced and frictional drags of the vertical surfaces. This usually results in a small net thrust from the vertical surfaces."
- Zdenek Titz and Jaroslav Zazvonil; "Kauba's Dwarfs", Flying Review International, Nov 1965, pp.169-172.
- Pohlmann (1982)
- Dan Sharp; Luftwaffe: Secret Wings of the Third Reich, Mortons, 2017, pp.68-73.
- Pohlmann (1982), p.193
- William C. Sleeman; "Preliminary Study of Airplane Configurations Having Tail Surfaces Outboard of the Wing Tips", RM L58B06, NACA 1958.
- M. Leroy Spearman and Ross B. Robinson; "Aerodynamic Characteristics of a Canard and an Outboard-Tail Airplane Model at a Mach Number of 2.01", RM L58B07, NACA, 1958.
- Paul G. Fournier; "Aerodynamic Characteristics of a Canard and an Outboard-Tail Airplane Model at High Subsonic Speeds", TN D-102, NACA 1961.
- Alford, W. J., Jr., Hammond, A. D., and Henderson, W. P.: "Low-Speed Stability Characteristics of a Supersonic Transport Model with a Blended Wing-Body, Variable-Sweep Auxiliary Wing Panels, Outboard Tail Surfaces, and Simplified High-Lift Devices", NASA TM X-802, 1963.
- Cornelius Driver, M. Leroy Spearman, and William A. Corlett, “Aerodynamic Characteristics at Mach Numbers From 1.61 to 2.86 of a Supersonic Transport Model With a Blended Wing-Body, Variable-Sweep Auxiliary Wing Panels, Outboard Tail Surfaces, and a Design Mach Number of 2.2,” NASA TM-X-817 (1963).
- "technology", FanWing. (retrieved 5 January 2018): " OHS Development (Outboard Horizontal Stabilizer) The recently developed TwinTail configuration, suggested originally by former BAE Systems Principal Concepts Engineer, George Seyfang, avoids the strong downwash flow directly behind the wing and exploits the upwash from the wingtip vortices. The new design has increased the efficiency of the aircraft by between 10 and 15% and also improved pitch stability."
- "July 2011: FanWing Modified TwinTail 2011", News, FanWing (retrieved 5 January 2018): "Following two series of wind-tunnel tests and analysis from January-June 2011 the newly modified TwinTail prototype was first flight tested June 18th and most recently July 16th 2011."
- Benjamin Darrenougue; "Aircraft Configurations With Outboard Horizontal Stabilizers" (Final year project report), Queens University Belfast, 14 May 2004.
- Kurt W. Muller; "Analysis of a Semi-Tailless Aircraft Design" (Master's thesis), Naval Postgraduate School, US, 2002.
- Pohlmann, Hermann. Chronik Eines Flugzeugwerkes 1932-1945. B&V - Blohm & Voss Hamburg - HFB Hamburger Flugzeugbau (in German). Motor Buch Verlag, 2nd Impression 1982 ISBN 3-87943-624-X.